RS485 dual-bus communication method used for test satellite

The invention discloses an RS485 dual-bus communication method used for a test satellite. The method comprises the following steps: a first RS485 bust and a second RS 485 bus are respectively connected between a satellite-borne computer utilized as a host machine and a lower computer utilized as a slave machine and between the satellite-borne computer and a measurement and control responser utilized as a salve machine; the host machine accesses the slave machines in turns by virtue of the first RS485 bus and the second RS485 bus, the slave machines respectively send response frames by virtue of the first RS485 bus and the second RS485 bus after receiving command frames sent by the host machine; and the host machine transmits data frames to the slave machines by virtue of the first RS485 bus and the second RS485 bus after receiving response signals.

Magnetic torquer electric simulator with function of fault simulation

The invention discloses a magnetic torquer electric simulator with a function of fault simulation, and relates to the field of satellite simulation tests. The invention solves a problem that a conventional mini satellite attitude control system is short of a device for simulating a fault function of a magnetic torquer. Three TTL receiving interfaces are respectively connected with three input ends of an input signal isolation circuit, and three output ends of the input signal isolation circuit are respectively connected with three input ends of an FPGA. The output end of a G485 fault receiving interface is connected with the input end of the FPGA, and the FPGA is sued for analyzing the type of a fault and achieving the pulse width collection and time delay of three-channel fault data. The three output ends of the FPGA are respectively connected with three input ends of an output signal isolation circuit, and three output ends of the output signal isolation circuit are respectively connected ...

PCM signal monitoring device with error detection alarming function and error detection alarming method thereof

The invention provides a PCM signal monitoring device with error detection alarming function and an error detection alarming method thereof and relates to a PCM signal monitoring device and an error detection alarming method; the invention solves the disadvantages that the existing device can not decode a PCM signal and can not carry out detection alarming to errors that a gating signal is laggedby a clock signal, the clock signal is lagged by a data signal, and the duty ratio of the clock signal is unbalanced possibly; after an external remote measuring or remote control detection signal isconverted by a signal isolation and level conversion module, the signal is transmitted to a remote measuring or remote control detection signal input end of a signal decoding and error detection alarming module through a remote measuring or remote control detection signal output end, and the signal decoding and error detection alarming module carries out detection alarming through a logic state machine ...

Satellite posture all-round controlling method based on magnetic moment device and flywheel

The invention discloses a satellite posture all-round controlling method based on a magnetic moment device and a flywheel, relating to an all-round posture controlling method for completing a satellite orbit-injection phase by using the magnetic moment device and the flywheel. The invention solves the problems of low reliability and short service life of the traditional satellite posture all-round controlling technology. The satellite posture all-round controlling method comprises the following steps of: 1, setting controller parameters according to the requirement of a control system; 2, measuring a geomagnetic field intensity vector Bb, a satellite angular velocity vector Wb and a solar azimuth, and sending the measured data to a satellite controller; 3, calculating an expected control moment vector Tm and a control magnetic moment vector Mm, and sending the control magnetic moment vector Mm to the magnetic moment device; 4, acquiring an effective solar azimuth vector Alfa; 5, calculating ...

Electric simulator for star sensor

The invention discloses an electric simulator for a star sensor, relates to an electric simulator for on-star equipment, and solves the problem that the conventional equipment or device cannot meet the requirement that the electric simulator of the star sensor and the star sensor are connected to a satellite test system simultaneously. The electric simulator comprises a functional simulation module, a simulator data interface circuit and a power supply input interface circuit, and also comprises a signal processing module, an on-star equipment data interface circuit and a power supply output interface circuit; an analog sensitive data signal output by the functional simulation module and a star sensitive data signal output by the on-star equipment data interface circuit are subjected to isolation synthesis processing in the signal processing module; the processed signal output end of the signal processing module is connected with the processed signal input end of the simulator data interface ...

Electric simulator of gyro

The invention provides an electric simulator of a gyro, and relates to an electric simulator of a satellite facility, which aims at solving the problem that an electric simulator of a gyro and the gyro can not be simultaneously connected to a satellite test system in an existing facility or device. The electric simulator comprises a functional simulation module, a simulator data interface circuit, a power supply input interface circuit, a data driven interface circuit, a signal processing module, a satellite facility data interface circuit and a power supply output interface circuit, wherein simulation sensitive data signals output by the functional simulation module and gyro signals output by the satellite facility data interface circuit are isolated and synthesized in the signal processing module, the processed signal output end of the signal processing module is connected with the processed signal input end of the simulator data interface circuit, and the voltage output end of the power ...

Housekeeping and attitude integrated on-board computer sequential control method

The invention discloses an on-board computer sequential control method, which comprises the following steps: establishing four related basic processes, namely a comprehensive management process, an attitude control input and output process, a bus communication process and an attitude control computing process; starting the comprehensive management process every other delta T seconds and synchronously starting the attitude control input and output process and the bus communication process; completing lower computer data acquisition and management functions through the bus communication process, acquiring attitude sensor data through the attitude control input and output process, synchronizing the attitude control computing process and performing attitude control output; and starting the attitude control computing process, and performing attitude control computing according to an attitude control computing input parameter to obtain an attitude control output parameter.

Redundant network design circuit of satellite commercial devices

The invention discloses a redundant network design circuit of satellite commercial devices, which comprises a plurality of commercial devices, a plurality of voltage stabilizing modules and an arbitration control circuit, wherein the commercial devices are interconnected through data buses to realize multiple functions, and any one function is fulfilled by at least two commercial devices; each voltage stabilizing module is connected with a commercial device; the arbitration control circuit is connected with the voltage stabilizing modules and the commercial devices respectively, and controls the enabling ends of the voltage stabilizing modules through collection of information of the states of the commercial devices so that the voltage stabilizing modules can supply power for the commercial devices stably. The redundant network design circuit of the satellite commercial devices realizes network design of satellite commercial devices, has a simple structure, and can improve the reliability ...

Testing task implementing and operating method of testing satellite

The invention discloses a testing task implementing and operating method of a testing satellite, which comprises the following steps: sending a testing task command from the ground to control the implementation of a satellite testing task, wherein the testing task command comprises a testing task, the implementation starting time of the testing task and the implementation finishing time of the testing task; comparing the current satellite time with the implementation starting time of the testing task, when the current satellite time and the implementation starting time of the testing task are the same, starting to implement the testing task and recording the obtained testing data through an electronic disk; comparing the current satellite time with the implementation finishing time of the testing task, when the current satellite time and the implementation finishing time of the testing task are the same or the recording of the data storage region of the electronic disk is full, stopping ...

Method for automatically testing steady state loss torque of flywheel

The invention discloses a method for automatically testing the steady state loss torque of a flywheel, relating to a testing method of the steady state loss torque of a flywheel, and solving the problems that the steady state loss torque of the flywheel has larger error because the rotation speed of the flywheel is manually controlled in the traditional flywheel steady state loss torque test, and the flywheel can not simulate a real attitude of satellite because the flywheel rotates in a rotation speed mode. The method for automatically testing the steady state loss torque of the flywheel comprises the steps of: firstly, controlling a computer to set an output torque, regulating the self rotation speed of the flywheel to reach the preset target rotation speed; secondly, controlling the computer to transmit a zero torque command to the flywheel, wherein the flywheel loses the torque and continuously rotates under the action of inertia; and thirdly, controlling the computer to obey a loss ...

Electric simulator of gyro

The invention provides an electric simulator of a gyro, and relates to an electric simulator of a satellite facility, which aims at solving the problem that an electric simulator of a gyro and the gyro can not be simultaneously connected to a satellite test system in an existing facility or device. The electric simulator comprises a functional simulation module, a simulator data interface circuit, a power supply input interface circuit, a data driven interface circuit, a signal processing module, a satellite facility data interface circuit and a power supply output interface circuit, wherein simulation sensitive data signals output by the functional simulation module and gyro signals output by the satellite facility data interface circuit are isolated and synthesized in the signal processing module, the processed signal output end of the signal processing module is connected with the processed signal input end of the simulator data interface circuit, and the voltage output end of the power ...

Optical imaging minisatellite attitude control system and in-orbit working mode switching method

The invention discloses an optical imaging minisatellite attitude control system and an in-orbit working mode switching method, belongs to the field of satellite attitude control and aims at solving the problem that existing optical imaging satellites cannot be simply and effectively switched in the orbit. The optical imaging minisatellite attitude control system comprises an attitude measurement sensor, an actuating mechanism and an attitude controller, wherein the attitude measurement sensor comprises a sun sensor, a star sensor and a gyroscope; the actuating mechanism comprises a counteraction flywheel and a magnetorquer. According to an in-orbit working mode switching method of the optical imaging minisatellite attitude control system, the optical imaging minisatellite attitude control system has six working modes, namely a rate damping mode, a sun capture mode, a sun-orientated three-axis stabilization mode, an earth-orientated three-axis stabilization mode, a data transmission mode ...

Flywheel based attitude maneuvering control device and method for successive approaching of satellite rounding instantaneous Euler shaft

The invention discloses flywheel based attitude maneuvering control device and method for successive approaching of a satellite rounding an instantaneous Euler shaft and relates to control device and method for satellite attitude adjustment. The invention is provided for solving the problems of great fuel consumption, short service life of a satellite, complex configuration of an air injecting control system and difficult reduction of size and weight of the satellite existing in the realization of satellite wide-angle attitude maneuvering by adopting air injecting control. The method comprises the following steps of: setting a parameter of the control device according to the system requirement of the control device and obtaining attitude deviation angular velocity according to a motion equation; and expressing a relationship of the instantaneous Euler shaft and a deviation angle of the current attitude and a target attitude of the satellite by an attitude error quaternion to obtain a control ...

Spacecraft bus router based on component-based module

The invention discloses a spacecraft bus router based on a component-based module, and relates to a spacecraft bus router, for solving the problem of low communication efficiency caused by communication difficulty among buses due to the mode of existence of the multiple buses of a conventional spacecraft. The bus router comprises a bus registration management module and an intermediate member data exchange module. The bus router respectively communicates with N components through the multiple buses, N being a positive integer. The bus registration management module is used for managing spacecraft bus registration, extracting bus component themes, managing component communication mapping tables among the buses according to the bus component themes and registering intermediate components. The intermediate component data exchange module comprises the multiple intermediate components for realizing data exchange among the intermediate components. The spacecraft bus router provided by the invention ...

Pico-nano satellite power supply achieved through maximum power point tracking technology

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 ...

Method for realizing satellite power control and modularized plug-and-play of distribution unit

The invention provides a method for realizing modularized plug-and-play of a satellite power control and distribution unit, belonging to the field of a satellite power supply system, and solving the problems that the research period of an existing satellite power supply system power control and distribution unit is long and the satellite task requirements cannot be rapidly responded to. According to the device, a lower computer and N extended function modules are assembled and integrated by a back plate; the lower computer and the N extended function modules realize data transmission through an inner bus circuit; the inner bus circuit comprises an inner bus main interface circuit, a module enabling coding simulation channel gating circuit and N inner bus sub-interface circuits; the inner bus main interface circuit is mounted in the lower computer; the module enabling coding simulation channel gating circuit is mounted in the back plate; each extended function module is internally provided ...

Sun vector measurement method and device thereof

Sun vector measurement method and device thereof

Pico-satellite satellite-borne power system achieved based on pure hardware

The invention provides a pico-satellite satellite-borne power system achieved based on pure hardware, and relates to the field of pico-satellite power sources. The pico-satellite satellite-borne power system solves the problems that an existing pico-satellite satellite-borne power system is poor in reliability and low in integration level. A solar cell array is used for converting solar energy into electric energy, providing primary energy and charging a storage cell, the power signal output end of a solar cell array controller is simultaneously connected with the power signal input end of a storage cell charging controller and the first power signal input end of a power switching controller, the power signal output end of the storage cell charging controller is connected with the first power signal input end of a storage cell protection device, the second power signal input and output ends of the storage cell protection device are connected with the power signal output and input ends of ...

Component agent module-based spacecraft interface adapter and data interaction method adopting adapter to realize

The invention relates to a component agent module-based spacecraft interface adapter and a data interaction method adopting the adapter to realize, and relates to the field of aerospace adapters. The invention aims to solve the problem that management use of an interface of an existing spacecraft generally adopts a method of display calling, in adoption of the method, interfaces of devices are not unified, thus device management and use are inflexible, and access of the component agent module to the devices is inconvenient, thereby causing poor universality. A device management unit is used for configuring device interfaces and realizing device interface registration, ID configuration and issuing/subscription of information of subjects, and the component agent module is used for registering interfaces and issuing/subscribing to subjects to a bus in the form of components according to device interface registration, ID configuration and issuing/subscription of information of the subjects ...

On-board equipment plug-and-play test interface circuit and method for realizing plug-and-play data transmission

The invention discloses an on-board equipment plug-and-play test interface circuit and a method for realizing plug-and-play data transmission and belongs to the field of satellite testing, aiming to solve the problem that test interfaces utilized between existing satellite ground test devices have no plug-and-play support functions and are low in test speed, thereby going against realizing plug-and-play between the on-board equipment and the ground test devices. A detection signal input end of a control circuit is connected with a detection signal output end of a connection state detection circuit, a power supply signal output end of the control circuit is connected with a power supply signal input end of a power supply output circuit, and a communication control signal input or output end of the control circuit is connected with an output or input end of a data transmission circuit. The detection circuit is used for detecting connection states between an on-board interface unit and a test ...

Electric simulator for star sensor

The invention discloses an electric simulator for a star sensor, relates to an electric simulator for on-star equipment, and solves the problem that the conventional equipment or device cannot meet the requirement that the electric simulator of the star sensor and the star sensor are connected to a satellite test system simultaneously. The electric simulator comprises a functional simulation module, a simulator data interface circuit and a power supply input interface circuit, and also comprises a signal processing module, an on-star equipment data interface circuit and a power supply output interface circuit; an analog sensitive data signal output by the functional simulation module and a star sensitive data signal output by the on-star equipment data interface circuit are subjected to isolation synthesis processing in the signal processing module; the processed signal output end of the signal processing module is connected with the processed signal input end of the simulator data interface ...

Low-orbit flexible satellite attitude tracking control method based on sliding-mode observer

The invention discloses a low-orbit flexible satellite attitude tracking control method based on a sliding-mode observer, relates to a low-orbit flexible satellite attitude tracking control method based on a sliding-mode observer, and aims at solving the problems that an existing low-orbit flexible satellite is low in satellite attitude tracking control accuracy due to relatively large aerodynamic interference torque and vibration of flexile components. The low-orbit flexible satellite attitude tracking control method based on the sliding-mode observer comprises the following steps: building a geocentric inertial coordinate system and a satellite body coordinate system; building a state space expression, and determining an upper bound of an interference signal received by the observer; solving a gain matrix of the observer, a matching matrix of the observer and a Lyapunov equation matrix variable; observing to obtain an estimated mode vibration velocity value of the sliding-mode observer ...

Locking and unlocking device for solar array

The invention provides a locking and unlocking device for a solar array, which is used for locking and unlocking the solar array and a space vehicle body structure, and comprises a first fixed part and a second fixed part, wherein the first fixed part is provided with a first through hole, a first caulking groove and a second caulking groove, the first caulking groove and the second caulking groove are respectively communicated with the first through hole; an electromagnet, a spacing spring assembly and a locking pin are sequentially installed in the first through hole; a cable and a connector which are electrically connected with the electromagnet are installed in the first caulking groove; a second through hole is arranged on one end part of the second fixed part, and the end part can be inserted into the second caulking groove of the first fixed part so that the second through hole and the first through hole are coaxial; and the locking pin can simultaneously penetrate through the first ...

Probe simulator of code disc type sun sensor

The invention provides a probe simulator of a code disc type sun sensor. The probe simulator comprises a processing unit, a communication unit, a digital-to-analogue conversion circuit, a voltage-dependent current source, a driving circuit and two quantity of state output units, wherein the communication unit is connected with the processing unit; a first output end of the processing unit is connected with an input end of the digital-to-analogue conversion circuit; an output end of the digital-to-analogue conversion circuit is connected with the input end of the voltage-dependent current source; a second output end of the processing unit is connected with the input end of the driving circuit; and the output end of the driving circuit is connected with the output ends of the two quantity of state output units. The probe simulator of the code disc type sun sensor provided by the invention can meet the test requirements of a processing circuit of the code disc type sun sensor; and the circuit ...

Method for automatically testing steady state loss torque of flywheel

The invention discloses a method for automatically testing the steady state loss torque of a flywheel, relating to a testing method of the steady state loss torque of a flywheel, and solving the problems that the steady state loss torque of the flywheel has larger error because the rotation speed of the flywheel is manually controlled in the traditional flywheel steady state loss torque test, andthe flywheel can not simulate a real attitude of satellite because the flywheel rotates in a rotation speed mode. The method for automatically testing the steady state loss torque of the flywheel comprises the steps of: firstly, controlling a computer to set an output torque, regulating the self rotation speed of the flywheel to reach the preset target rotation speed; secondly, controlling the computer to transmit a zero torque command to the flywheel, wherein the flywheel loses the torque and continuously rotates under the action of inertia; and thirdly, controlling the computer to obey a loss ...

Method for determining agile motor gesture of optical imaging satellite

The invention discloses a method for determining an agile motor gesture of an optical imaging satellite, relates to the field of determination of a satellite gesture, and aims at solving the problem that the gesture control accuracy of the satellite is reduced by large vibration generated by the existing satellite gesture determination method in determination of the calculation process at the early large-angle motor stage of the satellite gesture, thus an optical satellite imaging task cannot be smoothly carried out. The method comprises the following steps: 1, obtaining a system state equation and an observation equation according to the satellite gesture kinematic equation; 2, obtaining a gain matrix of a kalman filter according to the system state equation and the observation equation; 3, determining the agile motor gesture by using the kalman filter according to the change of filter parameters of the kalman filter. The method is applicable to determination of the agile motor gesture ...

Flywheel based attitude maneuvering control device and method for successive approaching of satellite rounding instantaneous Euler shaft

The invention discloses flywheel based attitude maneuvering control device and method for successive approaching of a satellite rounding an instantaneous Euler shaft and relates to control device and method for satellite attitude adjustment. The invention is provided for solving the problems of great fuel consumption, short service life of a satellite, complex configuration of an air injecting control system and difficult reduction of size and weight of the satellite existing in the realization of satellite wide-angle attitude maneuvering by adopting air injecting control. The method comprises the following steps of: setting a parameter of the control device according to the system requirement of the control device and obtaining attitude deviation angular velocity according to a motion equation; and expressing a relationship of the instantaneous Euler shaft and a deviation angle of the current attitude and a target attitude of the satellite by an attitude error quaternion to obtain a control ...