247 results about "Nano satellite" patented technology

The invention discloses a micro/nano satellite measure and control communication integral transmitting and receiving system and a realization method thereof. The method comprises the following steps: 1) uplink signal processing: 11) receiving and processing radio-frequency signals to obtain analog intermediate-frequency signals; and 12) carrying out analog to digital conversion and digital underlocking on the analog intermediate-frequency signals and dividing into two paths of uplink digital intermediate-frequency signals, namely, one path of the signals is sent to a satellite-mounted computer by QPSK (quadrate phase shift keying) demodulation and uplink protocol processing so as to finish uplink data transmission, and the other path of the signals is subjected to the PM (phase modulation) demodulation to obtain side sound signals and PSK (phase shift keying) remote signals, and the PSK remote signals are subjected to BPSK (binary phase shift keying) demodulation to convert into a remote control command which is sent to the satellite-mounted computer so as to finish the remote control; and 2), downlink signal processing: 21), acquiring two paths of data from the satellite-mounted computer and a storage unit, namely, one path of data which is subjected to downlink protocol processing, BPSK modulation, combination with the side sound signals and downlink measure and control carrier PM modulation is combined with the other path of data which is subjected to the downlink protocol processing and the QPSK modulation to enter a satellite-ground radio-frequency emission channel; and 22) converting into radio-frequency signals to finish the remote measure and the downlink data transmission.

The invention discloses separable micro and nano-satellite configuration which comprises a satellite body, a plurality of separate release sub-satellites, mechanical net claws, a flexible solar cell array and a variable-structure mechanical arm. The separable micro and nano-satellite configuration has the advantages that the integral separable micro and nano-satellite configuration is in such a configuration form that a primary satellite carries the multiple sub-satellites, and functions of separately releasing and hovering the micro and nano-satellites can be realized; the efficiency of the solar cell array can be improved owing to combined configuration comprising flexible solar wings and the variable-structure mechanical arm; mechanical net claw mechanisms are carried on the micro and nano-satellites, so that a function of capturing space targets can be realized; the separable micro and nano-satellite configuration is provided with a plurality of stereoscopic vision imaging cameras, so that a stereoscopic monitoring function can be realized; attitude maneuver and attitude stabilization of the micro and nano-satellites can be implemented by the aid of a solid miniature propulsion technology, so that the sub-satellite separate release control ability can be improved; the separable micro and nano-satellite configuration is applicable to fifty-kilogram-level micro-miniature artificial earth satellites on near-earth orbits and is also applicable to micro-satellite networking, scientific detection aircrafts and relevant micro and nano-satellite space demonstration and experiments.

The invention discloses a child-mother satellite space debris clearing platform. The child-mother satellite space debris clearing platform includes a plurality of child satellites for clearing space debris; each child satellite is detachably connected the same mother satellite; the mother satellite is used for driving the child satellites to move among a multiple pieces of space debris; a space debris clearing device is arranged on each child satellite; and each space debris clearing device includes a child measurement device for measuring a pose of the space debris and a child satellite capturing device. A microsatellite is used as the mother satellite, and a plurality of micro-nano satellites are used as the child satellites; operations such as orbit transferring, closing and detailed survey, and capturing and de-orbiting can be completed coordinately; the child-mother satellite space debris clearing platform is low in cost, is fast in response speed, and is high in reliability; after the child satellites are released, the combined space debris observation network can acquire accurate debris pose information through coordinate observation; and the child satellites can independently complete de-orbiting operations, the mother satellite can directly go to next space debris to be cleared, time and energy can be saved, the benefits of space debris clearing can be increased, and the cost is reduced.

A deployable and tracked solar array mechanism for restraining and releasing deployable solar panel arrays on a spacecraft is provided. The mechanism comprises a solar array drive mountable to the top side surface of the spacecraft. A solar panel array is pivotally attached to the solar array drive and positionable against the spacecraft. At least one notch is formed in at least one of the side edges of the solar panel array. A frame is slidably mounted to the spacecraft around the solar panel array. At least one tab extends from the frame over the solar panel array and releasably restrains the solar panel array. A spring mechanism urges the frame in a direction generally away from the solar array drive assembly. A release mechanism holds the frame against the force of the spring means wherein upon initiation of deployment, the release mechanism disintegrates allowing the spring means to slidably urge the frame in a general direction away from the solar array drive assembly thereby aligning the at least one notch with the at least one tab and releasing the solar panel array from against the spacecraft.

The invention discloses a micro/nano-satellite low-voltage efficient power supply system. A 12V low-voltage unregulated bus topological structure is adopted, a lithium ion storage battery pack is used as an energy storage device, and a shunt regulating manner is adopted to realize power regulation and voltage stabilization as well as constant current-constant voltage charging for the storage battery pack. Solar battery packs are in grouping connection, and correspond to direct power supply and shunt power supply respectively; fault isolation is designed in a shunt circuit, and when the system judges that the shunt circuit breaks down, a group of switches backup for the shunt circuit respectively realize bus stabilization and a constant-voltage charging function for the storage battery pack; satellite power-up begins to work when a satellite power supply interface can realize satellite-socket separation; and charging management and overcharging protection can be carried out in different life periods. The power supply system disclosed by the invention has the characteristics of low power consumption, small size and light weight, and can be applied to micro/nano-satellite power supply systems with the whole-satellite load power consumption of 5 to 100 W.

The invention discloses a Pico/Nano satellite and rocket fixing and separating device. The Pico/Nano satellite and rocket fixing and separating device comprises a bottom plate. Satellite supporting bases, pull rods, pull rod cut-off mechanisms and satellite popping mechanisms are fixed to the bottom plate. At least one pair of satellite supporting bases is arranged. Any one pair of satellite supporting bases is oppositely arranged in pairs. At least one pair of pull rods is arranged. Each pair of pull rods is installed in any one pair of satellite supporting bases respectively. Each pull rod stretches out of a satellite supporting face of the corresponding satellite supporting base to be connected with a satellite and presses the satellite on the satellite supporting face. According to the Pico/Nano satellite and rocket fixing and separating device, when the satellite and the bottom plate are connected, pull force and pressure exerted on the bottom plate are exerted on the same straight line, and therefore the interaction force between the bottom plate and the satellite is reasonably distributed, the integral structure is simple and stable, meanwhile, installing is convenient, and the manufacturing cost is low.

The invention provides an electromagnetic butting device for micro/nano satellites capable of rotating after being butted and a butting method. The device is mounted on micro/nano satellites and leads two micro/nano satellites to be accurately butted. The device comprises an active butting mechanism and a passive butting mechanism, wherein one end of the active butting mechanism is in the shape of a horn, a permanent magnet synchronous motor and a circle of active butting teeth are arranged in the active butting mechanism, and the permanent magnet synchronous motor drives the active butting teeth to rotate; the main body of the passive butting mechanism is in the shape of a circular truncated cone which is matched with the horn-shaped port of the active butting mechanism, and a circle of passive butting teeth are arranged in the passive butting mechanism; and after the active butting mechanism and the passive butting mechanism are butted, the active butting teeth and the passive butting teeth are meshed, and when the permanent magnet synchronous motor works, the active butting mechanism and the passive butting mechanism rotate oppositely. The device provided by the invention is small in volume, light in weight and high in reliability and can be applied to micro/nano satellites so as to enable the micro/nano satellites to realize one-dimensional rotation. After multiple micro/nano satellites are freely butted and combined, configuration transformation of a combined body is realized, and splicing and superposition of an observation field are completed, thereby being favorable for realizing multi-angle earth observation of the micro/nano satellites.

The invention discloses a liquid ammonia propulsion system for a pico-satellite or a nano-satellite. The liquid ammonia propulsion system comprises a digital signal processing circuit and a micro-propulsion device, wherein the micro-propulsion device comprises a propulsion system storage tank used for storing liquid ammonia, a thruster communicated with the propulsion system storage tank, and a solenoid valve mounted between the propulsion system storage tank and the thruster; the digital signal processor comprises an information monitoring module, a control switch module and an interface communication module; the information monitoring module is used for monitoring the current operation state of the propulsion system; the control switch module is used for controlling the solenoid valve so as to turn on or turn off the thruster; the interface communication module is used for feeding back information on the current operation state of the propulsion system to the satellite and receiving remote control commands sent by the satellite. The liquid ammonia propulsion system has the characteristics of small size, light weight, low power consumption, high specific impulse, simple structure, short development period, high safety performance, multi-functional integration, space plug and play function, universal applicability to 10 kg-magnitude pico-satellites and nano-satellites, and the like.

The invention discloses a satellite housekeeping simulator and a satellite housekeeping simulation method for development and test of a micro-nano satellite control module. The satellite housekeeping simulator adopts an integrated functional design and a generalized interface design, comprises satellite housekeeping simulator hardware, a command file and a satellite housekeeping simulator application program, wherein the satellite housekeeping simulator hardware is used for running the satellite housekeeping simulator application program and establishing data communication with an external system; the command file is responsible for describing commands, a command sequence, data blocks and a data block sequence used in control module tests; and the satellite housekeeping simulator application program is responsible for driving a board card to operate, reading the command file, processing bus communication data, executing and managing testing process and the like. The satellite housekeeping simulator disclosed by the invention has good flexibility and high universality, can support the control modules (in different development completion degree stages) of the micro-nano satellites of different types to conduct tests, and satisfies the requirements for ''simultaneous design and testing'' of the micro-nano satellite; in addition, the satellite housekeeping simulator has a certain degree of automated testing capability.

A nano satellite remote-measuring and remote-controlling method capable of switching communication path relates to a satellite remote-measuring and remote-controlling processing method. Without increasing the cost and the complexity of the satellite, the ground also can remotely measure and control the satellite when a malfunction occurs on an on-board computer. In this method, through detecting whether the updating frequency and the communication of remote-measuring data sent by the on-board computer of a satellite system is normal or not, a ground tracking telemetry control station judges whether a malfunction occurs on the on-board computer or not; when a malfunction occurs, the ground tracking telemetry control station directly communicates with a plurality of sub-systems of the satellite through a measuring and controlling sub-system. The method provided by this invention is applicable to the remote-measuring and remote-controlling data transmission of the nano satellite.

The invention discloses a control method for a nano satellite magnetic torquer space temperature compensation attitude. The control method specifically comprises the following steps that first, a system and an orbital coordinate system are built separately; second, in the despinning process, nano satellite attitude parameters and magnetic torquer parameters are obtained, and a despinning control law based on temperature compensation is built; third, in the capturing process, nano satellite attitude parameters and magnetic torquer parameters are obtained and subjected to optimizing treatment, and accordingly an attitude capturing control law based on temperature compensation is built; and fourth, a magnetic torquer is controlled by means of the despinning control law based on temperature compensation and the attitude capturing control law based on temperature compensation so as to control the satellite attitude. The control precision of the satellite attitude is improved by adopting a temperature compensation method, so that the control period is shortened, and validity is verified; and compared with a nano satellite system without temperature control, by using the method, good engineering application prospects are achieved, and wide ideas are supplied to low-cost microsatellite development.

The invention provides a mini high-functional-density integrated satellite electronic system which is high in functional density, expansibility and standard degree. The system is applied to a 10kg, 50kg or 100 kg micro/nano satellite, and comprises a core board card and an expanded board card which communicate with each other via a high-speed interconnection bus. The expanded board card is connected with satellite hardware equipment via interfaces, concretely, connected with a microwave network interface of a satellite antenna, a load interface of a satellite load, an analog collection interface of a satellite single-end analog collector, an instruction interface of instruction reception, a primary bus interface of a satellite storage battery, a power driving interface of a power driver, aheat control loop interface of heat control equipment and a sensor interface of a sensor. The core board card obtains data of the satellite hardware equipment via the expanded board card to realize functions including satellite affair management, attitude and orbit control, measurement and control, navigation, data transmission and power supply management.

The invention provides a measurement, control and data transmission integrated system for micro-nano satellites, which comprises a measurement, control and data transmission integrated module, a processor module and a load module, and is characterized in that the processor module sends satellite telemetry data to the measurement, control and data transmission integrated module and receives telemetry quantity acquisition data of the measurement, control and data transmission integrated module; the load module receives the upper injection data of the measurement, control and data transmission integrated module and returns load data to the measurement, control and data transmission integrated module; the measurement, control and data transmission integrated module comprises a to-the-sky transceiver module and a to-the-ground transceiver module. The independent design of multiple single machines of a traditional satellite measurement and control and data transmission subsystem is replaced,the functions of measurement and control, data transmission, storage and the like are integrated, the functions of measurement and control and data transmission are achieved at the same time throughthe same channel, miniaturization, integration and simplification design of microsatellites is facilitated, the application efficiency of a ground measurement and control network is improved. The method is a future satellite-ground communication development trend.

The invention provides a free reconstitution and cooperative observation earth observation nano-satellite cluster system. The system comprises four same nano-satellites and has two basic states of a dispersed state and an aggregation state. In the dispersed state, through intelligent cooperation of the four satellites, five types of cooperative earth observation under three formation configurations can be achieved and includes vertical orbit splicing observation, multi-target observation, along-track splicing observation, relay staring observation and same-target multi-angle observation. In the aggregation state, the four satellites are freely docked to achieve different structures of a combination, so that an observation view field is spliced and superposed. Through intelligent cooperation of the dispersed state and free reconstitution of the aggregation state, the task flexibility of the nano-satellite cluster system is greatly improved, and the system can further meet the application requirements of wide-area observation, data fusion and the like. The system solves the problems that a traditional earth observation system is poor in flexibility, high in cost and the like and canbe applied to earth observation with various task requirements.

The invention relates to the technical field of temperature control of satellites, in particular to a pico/nano satellite heat flow infrared cage. The pico/nano satellite heat flow infrared cage comprises a satellite, baffles and infrared cage devices, wherein the satellite is of a cube structure; the infrared cage devices are of a rectangular sheet structure; one infrared cage device is arranged outside each side face of the satellite; the baffles are arranged between the side faces of the satellite and the infrared cage devices correspondingly; each infrared cage device is parallel to and concentric with the corresponding side face of the satellite; each side edge of each infrared cage device is L longer than the corresponding side face of the satellite, specifically, L is 100-200 mm; and the side edge of one end of each baffle is fixedly connected with the corresponding side edges of the infrared cage devices, and the side edge of the other end of each baffle points to the corresponding side edge of the satellite. The pico/nano satellite heat flow infrared cage meets the requirement for pico/nano satellite heat flow simulation, the heat flow uniformity of each surface is smaller than 5%, and heat flow simulation of the infrared cage for pico/nano satellite heat balance testing is achieved.

The invention relates to a spacecraft coplanar formation accompanying-flight configuration control method. The spacecraft coplanar formation accompanying-flight configuration control method comprises that in dependence on analytical solutions of a C-W equation, an expression of geometric parameters of the configuration is obtained; in the expression, geometric parameters representing relative movement characteristics serve as control objects, and the control objects comprise an ellipse center radial position xc, an ellipse center transverse position yc, an ellipse semi-minor axis b and a phase [theta] of a spacecraft on a relative movement ellipse; and the control objects are controlled based on a minimum fuel control theory. By employing the spacecraft coplanar formation accompanying-flight configuration control method, fuel can be saved, and the spacecraft coplanar formation accompanying-flight configuration control method is suitable for controlling on-board independent coplanar formation configurations of micro/nano-satellites in the magnitude of hundred meters to tens of kilometers, having satellite-to-satellite real-time relative measurement and constrained by resources.

The invention discloses an ionospheric photometer suitable for a micro/nano satellite platform, which comprises a hollow parabolic reflector, an MCP-type anti-vibration detector and a circuit board, wherein the reflector and the detector are sequentially arranged in the circuit board and light incident to a reflector plate is made to be gathered to the detector; the detector comprises a supportingframe and a BaF2 crystal window, a microchannel plate, a detector anode and a high voltage power supply in the frame; after the light passes through the BaF2 crystal window to filter stray light, photoelectric conversion and electron multiplication are carried out through the microchannel plate, and through the detector anode, multiplied charge cloud signals are received. The weight of the existing photometer is reduced from more than 5Kg to less than 1Kg, the volume is decreased by more than 50%, photon filter losses are reduced, the sensitivity of the instrument is increased by more than 30%, batch processing is facilitated, and the batch production cost is reduced.

The invention discloses a flywheel mechanism for a micro/nano-satellite, relates to a flywheel mechanism and aims at solving the problem that the micro/nano-satellite in the prior art is not provided with a flywheel which is short in manufacturing period, simple in structure, low in cost and reliable in performance. The flywheel mechanism comprises a motor support, a damping cushion, a brushless motor, a wheel body and a protective cover, wherein the damping cushion is a rectangular frame body; a through hole for mounting the motor is formed in the rectangular frame body; the damping cushion is arranged on the motor support; the brushless motor is arranged on the motor support; the damping cushion is arranged between the brushless motor and the motor support; the output end of a rotating shaft of the brushless motor is sleeved by the wheel body; and the protective cover is arranged on the motor support and is buckled outside the wheel body. The flywheel mechanism is used for the fields of flight and spaceflight.

The invention discloses a satellite and rocket adapter device used for micro/nano satellite vibration attenuation. Satellite and rocket mechanical interface adapting and satellite system level vibration attenuation are integrally designed, the satellite and rocket adapter device suitable for 1kg-50 kg-level micro//nano satellite vibration attenuation can meet connection adapting of a circular ringtype micro/nano satellite unlocking mechanism and a rocket support and also has good vibration attenuation performance and anti-impact performance so that the mechanical environment of a micro-nano satellite launching section can be effectively improved; and meanwhile, according to the satellite and rocket adapter device, a set of simulated analysis and verification test flow with a complete system is formulated for optimization of appropriate rigidity of upper/lower anti-vibration pads, the optimization for the rigidity of the anti-vibration pads is formulated to meet the special environmentrequirement of aerospace application.