248 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 satellite-borne AIS and ADS-B integrated receiver based on a micro-nano satellite. The satellite-borne AIS and ADS-B integrated receiver sysstem comprises an antenna module,a radio frequency front end module and a digital signal processing module composed of a high-speed analog / digital converter and a system-on-chip SoC, and And synchronous receiving and efficient processing of the AIS and ADS- B signals are achieved. The receiver receives the mixed signals of AIS and ADS-B and performs RF filtering amplification on the signals.; the obtained signal is sent to a signal processing unit and is sampled by a high-speed analog / digital converter; the message is input into a SoC platform to carry out digital down conversion, signal separation and decimation filtering, and frame header burst detection, frequency offset estimation, signal demodulation, data decoding and other processing are carried out on the obtained message and then CRC (Cyclic Redundancy Check) iscarried out, and finally the required AIS (Automatic Identification System) and ADS-B data are obtained. The integrated receiving design is adopted, the size and weight of on-satellite loads and the power consumption of a receiver are effectively reduced, high integration is achieved, and the method is more suitable for being applied to micro-nano satellites.

The invention provides a separation self power on and battery protection method applied to a micro / nano satellite. The satellite can be kept in a power-off state during a satellite launching process, and the energy loss of the battery is reduced, and after the satellite and a loader are separated, a separation switch is on, a battery pack is automatically connected onto a power supply bus, and power is provided for the satellite load. The separation switch only controls the gate of an MOS transistor as a discharging switch, the passing current is small, and a derating design does not need to be considered; due to a necessary redundancy design, a risk that connection between the battery pack and the power supply bus is broken due to failure of the separation switch during the in-orbit operation period of the satellite can be prevented. Over charging and over discharging protection functions are provided, the battery pack can only perform charging but not discharging after over discharging protection happens to the satellite, and after the voltage rises to a certain value, the battery can be reconnected onto the power supply bus for providing power for the load through software control. The method of the invention is simple and reliable, self power on work after the satellite and the loader are separated can be realized, and energy loss in the transmission section is reduced.

The invention discloses a rope tied nano satellite system for space debris capturing. The rope tied nano satellite system comprises a launching platform, two nano satellites and a tying rope. The launching platform is used for carrying the two nano satellites and launching the two nano satellites towards space debris during space debris capturing. A buffering material is attached to the surface of each nano satellite. The two ends of the tying rope are separately connected with the two nano satellites. The tying rope is contained in the launching platform before the two nano satellites are launched and is unfolded and winds or encases the space debris to capture the space debris under traction of the nano satellites after the two nano satellites are launched. The rope tied nano satellite system has the advantages that the rope tied nano satellite system is adopted to capture the targets, and the targets in any shape can be captured through the flexible tying rope; and the nano satellites are provided with buffering materials, and the situation that the nano satellites and the targets are damaged due to collision between the nano satellites and the targets can be avoided; the tying rope has a bonding and buckling function, a magnetic attraction function, a shape memory function and an automatic tightening function, and the targets can be prevented from escaping; and compared with other capturing modes, the rope tied nano satellite capturing system has higher economic benefits.

The invention provides a device and a method for controlling a flight attitude of a micro / nano satellite. The device comprises a fuzzy adaptive PI (Proportional-Integral) controller, a driver, a high power density motor and a flywheel body, wherein the fuzzy adaptive PI controller is used for sending an adjustable duty ratio pulse signal to the driver; the driver is connected with the fuzzy adaptive PI controller, and used for converting the adjustable duty ratio pulse signal into an angular momentum control signal and sending the angular momentum control signal to the high power density motor; the high power density motor is connected with the driver, and used for controlling the flywheel body according to the angular momentum control signal; and the flywheel body is connected with the high power density motor, and used for outputting variable angular momentum under the driving of the high power density motor to control the flight attitude of the micro / nano satellite. The device for controlling the flight attitude of the micro / nano satellite has the advantages that the device can adaptively absorb various disturbing moments during an on-orbit period, responds at superspeed, is high in accuracy, has a zero tracking error, and can adaptively resist external disturbance.

The invention discloses an integrated power system for a nano satellite. The system comprises a solar battery array, a storage battery group and a power controller. The solar battery array is used for converting solar energy into electrical energy to charge the storage battery group or output electricity for loads; the storage battery group is connected with the solar battery array in parallel, and used for storing the electrical energy converted by the solar battery array or outputting electrical energy to supply power for the loads; the power controller is used for regulating and stabilizing the current or voltage transmission among the solar battery array, the storage battery group and the loads; and the storage battery array is directly connected with the power controller by an electrical connector. The integrated power system for the nano satellite has the characteristics of using fewer cables, and being small in volume, high in integration level and excellent in reliability.

The invention relates to a micro / nano satellite universal testing system based on a PXI bus, wherein the system belongs to the technical field of satellite testing. The testing system comprises a PXIhardware subsystem and an upper computer in which LabVIEW software is installed. The PXI hardware subsystem performs communication with the upper computer and a tested object through a serial port busand a CAN bus. The PXI hardware subsystem comprises a PXI cabinet, a master controller, a signal conditioning module, a data acquisition module and a CAN communication module. The master controller,the signal conditioning module, the data acquisition module and the CAN communication module are integrated in the PXI cabinet and are connected with the PXI cabinet through a PXI cabinet backboard bus. The master controller controls and schedules each functional module board through a PXI / PXIe blended backboard bus. The micro / nano satellite universal testing system has advantages of high versatility, high system software degree, and high testing system architecture flexibility. The micro / nano satellite universal testing system can satisfy different testing requirement and quick and low-cost developing characteristics of each module in the developing period of the micro / nano satellite and furthermore has automatic testing capability.

The invention discloses a deorbiting device for a micro / nano satellite. The deorbiting device for the micro / nano satellite comprises a sail storing device, a sail unfolding device and an unlocking device, wherein the sail unfolding device is of a centrosymmetric structure, and comprises an upper end cover, a lower end cover, a clack-shaped central shaft, two ring flanges, two strip elastic masts, four supporting prisms, four pairs of pilot sleeves, four hold-down mechanisms and four leaf springs. After a ground command is received, the unlocking device releases the clack-shaped central shaft of the sail unfolding device; the strip elastic masts wound on the clack-shaped central shaft drive a thin-film sail, which is stored in a sail storing chamber, to unfold through releasing elastic potential energy stored by the strip elastic masts. According to the deorbiting device for the micro / nano satellite, the normal sectional area, in which a satellite moves, is increased by utilizing the unfolding of the thin-film sail, the effect of atmospheric drag perturbation on the micro / nano satellite is enhanced, and thus, the passive deorbiting of the micro / nano satellite is prompted.

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 heat sink simulator for nano-satellite space, which comprises an analogue unit, a data acquisition unit, a controller, a power driving unit and a communication unit. The analogue unit comprises a thermoelectric refrigeration sheet TEC, a heat flow sensor, a fan, a temperature sensor A, a temperature sensor B and fins; and the controller generates control signals of the TEC according to a feedback heat flow value acquired by the data acquisition unit and a given heat flow value as input of an algorithm controller, achieves good tracking of given heat flow by the feedback heat flow, namely, achieves good simulation of spatial radiation heat flow by heat conduction flow, transfers the heat led out by the TEC to the fins at the same time of ensuring heat flow tracking, achieves control of temperature of the fins by the fan according to control demand, radiates redundant heat to the air, and achieves simulation of spatial low temperature and black background environment. The heat sink simulator has the advantages of little thermal inertia, quick response speed and small volume, and achieves desktop representation of a nano-satellite heat test device.

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 pico-nano satellite power supply achieved through the maximum power point tracking technology and relates to the field of satellite power supplies. The pico-nano satellite power supply solves the problem that most of existing pico-nano satellite power supply systems are controlled through software and accordingly software defects lead to system failures. The power supply signal output end of a solar battery pack is connected with the power supply signal input end of a maximum power point tracking controller, the control signal output end of the maximum power point tracking controller is connected with the first control signal input end of a charge controller, the second control signal input and output end of the charge controller is connected with the first control signal output and input end of a storage battery protector and then connected to a bus, the second control signal input and output end of the storage battery protector is connected with the power supply signal output and input end of a storage battery pack, the control signal input end of a direct voltage conversion unit is connected to the bus, and the control signal input end of a power distribution unit is connected with the bus and the control signal output end of the direct voltage conversion unit at the same time and outputs voltage. The pico-nano satellite power supply is applied to supplying power to a pico-nano satellite.

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 discloses a micro / nano-satellite reaction flywheel control method based on linear Hall. The method comprises the steps of (1) acquiring an electrical angle theta and an angular velocity omega at a rotor position of a reaction flywheel motor from output signals of three linear Hall sensors distributed uniformly along the same circumference; and (2) obtaining a reference signal of a three-phase current control instruction for a stator of the reaction flywheel motor from the output signals of the three linear Hall sensors, thus controlling a reaction flywheel. The micro / nano-satellite reaction flywheel control method based on linear Hall is low in cost, stable in control effect and high in driving efficiency.

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 space target characteristic measuring and reconnaissance method for micro-nano satellite group approaching reconnaissance. The method comprises a task preparation stage and a task execution stage, the task preparation stage comprises the following steps: taking space target characteristic measurement as a target, combining the maneuvering capability and the load detection capability of a micro-nano satellite, decomposing a working task target and capability requirements of a single satellite, and constructing a satellite group based on the working task target and the capability requirements; the task execution stage comprises migration maneuvering, approaching reconnaissance and the like. According to the invention, an inter-satellite intelligent, cooperative and autonomous working mode demonstration is established, the method can be popularized and applied to the fields using formation / satellite group / constellation, such as on-orbit maintenance, space-based communication and earth remote sensing, and the modes and methods of measurement, control and working of space satellites in the future are greatly changed; space target characteristic measurement is carried out through star group approaching reconnaissance, a task execution work flow is given and serves as a novel data source of target characteristics, in-orbit view angle target characteristic information urgently needed by space application can be provided, the blank of target characteristic information acquisition in related fields is filled in time, and the target characteristic information acquisition efficiency is improved. And the capability of entering the space and utilizing the space is greatly improved.

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.