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.

Pulsar signal detector based on single event effect

The invention discloses a pulsar signal detector based on single event effect, relating to the technical field of data processing and solving the problems of support defect of low-pressure high-vacuum and low-temperature environment and overlarge detection area of the traditional detector. The pulsar signal detector comprises a register unit array comprising M+1 register units and an adder array comprising M adders, output ends of the first register unit and the second register unit are respectively connected with the first input end and the second input end of the first adder, the output end of the first adder is connected with the first input end of the second adder, the output end of the third register unit is connected with the second input end of the second adder, the carry output end of the first adder is connected with the low-level carry input end of the second adder, by suck analogy, the output end of the mth adder is connected with the first input end of the (m+1)th adder, the ...

On-line restoration method of permanent fault circuit of reconfigurable satellite-borne computer

The invention provides an on-line restoration method of a permanent fault circuit of a reconfigurable satellite-borne computer, which relates to the technical fields of space flight and aviation and solves the problem that irreparable damage generated by an FPGA circuit in a traditional reconfigurable satellite-borne computer under the influence of space radiation causes a permanent circuit faultdirectly. The on-line restoration method comprises the following steps of: firstly, determining an FPGA circuit generating a permanent circuit fault by a radiation hardening processor, then starting using the other FPGA circuit to work by the radiation hardening processor and finally, carrying out on-line restoration on the FPGA circuit generating the permanent circuit fault by the radiation hardening processor. The invention is suitable for reconfigurable satellite-borne computers.

Double-processor borne computer

The invention discloses a double-processor borne computer which relates to a double-processor technology applied in the aerospace field. The double-processor borne computer solves the problem that ping pong switch and ping-pong right robbing are difficult to avoid in the arbitration method in a borne computer of the traditional double-processor borne computer. A master computer, a slave computer,a power supply, an arbitration module and an IO module of the double-processor borne computer are all fixed on a base plate and connected mutually through data address buses, signal wires and power wires on the base plate, wherein the logical relation of the arbitration module is that: the working condition of the master computer is that an star arrow separation signal is ineffective, an output enable signal of the slave computer is ineffective, and a ready signal of the master computer is effective, or a remote control switch master computer signal is effective; and the working condition of the ...

Device and method for testing superconductivity of three-dimensional low-temperature superconducting thin film coil

The invention relates to a device and method for testing the superconductivity of a three-dimensional low-temperature superconducting thin film coil, belonging to the field of a low-temperature superconductivity technology and high-accuracy measurement. Particularly, the superconductivity test is carried out on the three-dimensional low-temperature superconducting thin film coil, the superconductivity of the three-dimensional low-temperature superconducting thin film coil is tested and researched by means of a vacuum and low-temperature environment provided by a low-temperature environmental system and a vacuum environmental system provided by the invention, and further the three-dimensional superconducting thin film coil is designed in an auxiliary manner. The invention designs a low-temperature system for testing the superconductivity of the three-dimensional low-temperature superconducting thin film coil, therefore, a low-temperature environment needs to be provided for superconducting ...

Sine-cosine function IP core capable of reconfiguring spaceborne computer and control method thereof

The invention relates to a sine-cosine function IP core capable of reconfiguring a spaceborne computer and a control method thereof, relating to the technical field of aerospace electronics, and solving the problems that the result of initial value assignment is largely influenced due to rounding errors, and the larger the angle is, the more the iteration times is needed. An initializing module is connected with a right-shift N-bit module and a module 1, the module 1 is connected with a cosine value storing device, the right-shift N-bit module is connected with a sine value storing device, the cosine value storing device and the sine value storing device are connected with a subtracter-adder and a first multiplier, the subtracter-adder is connected with a second multiplier and then is connected with the cosine value storing device, the first multiplier is connected with a left-shift 1-bit module and then is connected with the sine value storing device, and the a controller is connected ...

Semi-physical simulation system for attitude control of star-arrow integrated spacecraft

The invention discloses a semi-physical simulation system for attitude control of a star-arrow integrated spacecraft, which relates to the semi-physical simulation system for control of the star-arrow integrated spacecraft. The invention solves the problem that the conventional semi-physical simulation system for the attitude control of the spacecraft cannot simulate the spacecraft from a launching point to an active operation stage attitude control system. A simulation signal input or output end of a real-time simulator is connected with a simulation signal output or input end of an onboard computer; a wireless signal input or output end of a stage wireless communication module is connected with a wireless signal output or input end of the real-time stimulator; and a signal output or input end of a ground wireless communication module is connected with a signal input or output end of a ground control module. The system is suitable for the stimulation of the attitude control of the star-arrow ...

Formation satellite attitude cooperative control simulating device and simulation verification method thereof

The invention relates to a formation satellite attitude cooperative control simulating device and a simulation verification method thereof, which belong to the field of aerospace and aims and solve the problem that a traditional satellite attitude cooperative control problem only can be stopped on the level of mathematical simulation. The device comprises a basic platform unit, n air-floating rotary table systems, a camera positioning system and a ground control unit, and the simulation verification method which is carried out on the basis of the device comprises the following steps of: issuing a control instruction by a ground control computer according to a scheme and computing control torque by a PC104 simulation computer; designing a torque distribution method for a thruster, and carrying out simulation by an air-floating rotary table according to the set scheme; transmitting the information of a camera after photo taking to a photo processing computer to obtain angle information; acquiring ...

Multi-core onboard spacecraft computer based on FPGA

The invention relates to a multi-core satellite-bone computer, belonging to the data processing technical field of aerospace and aiming at solving the problem of slow processing speed of the satellite-bone computer by adopting an ASIC software realization mode. The satellite-bone computer comprises an FPGA based on an SRAM, n PROMS, n SRAMS, an anti-fuse FPGA and a configuration NOR type flash memory, wherein the FPGA based on the SRAM forms a multi-core structure with n processors, the anti-fuse FPGA comprises a read-back brush write interface circuit, a monitoring circuit and a control circuit, the monitoring circuit monitors the health state of the n processors, if an abnormal part needs reconstruction, the read-back brush write interface circuit reads the configuration file of the FPGA based on the SRAM at set speed, compares the configuration file of the FPGA with an original configuration file, and reconstructs the error parts if different. The multi-core satellite-bone computer can ...

Satellite attitude orienting system and method

The invention relates to a satellite attitude orientation system and a method thereof. A quaternion product unit inside the system adopts a hardware description language to design a hardware circuit, and a parallel calculation module is obtained; the parallel calculation module is utilized to carry out quaternion product operation of quaternion attitude parameters q<(1)> and q<(2)>, and a quaternion attitude parameter q' of a satellite reference system O mu v omega relative to a reference system Oxyz is obtained; and satellite attitude relative to a reference object can be determined according to q'. The method comprises: controlling data flow in each part of a control data path of a state controller; generating signal for loading, reading and shifting a register; and parallelly finishing quaternion product operation. The method can greatly increase the speed of quaternion operation in the orientation system, and can determine satellite attitude relative to a reference object at faster ...

Control circuit of air-supporting rotating platform nozzle switch

The invention relates to a control circuit of an air flotation rotary table nozzle switch, in particular to a control circuit of a nozzle switch. The invention solves the problem that the damage of an operational amplifier and a peripheral circuit easily causes damage to an upper simulation system computer thereof in the existing control circuit of the air flotation rotary table nozzle. In the control circuit, a signal output end of an upper simulation system computer is connected with a signal input end of a CAN bus, a signal output end of which is connected with a signal input end of a singlechip; and a driving signal output end of the singlechip is connected with an input end of a limited current circuit, an output end of which is connected with a signal input end of a power amplifier. The control circuit is applicable to the control process of the movement of the air flotation rotary table.

Simple simulation device and simulation method applied to star sensor of single-shaft air-floating platform

The invention relates to a simple simulation device and a simple simulation method applied to a star sensor of a single-shaft air-floating platform, which solve the problems that the star sensor in the semi-physical simulation of a conventional ground spacecraft cannot access a simulation system and then cannot test the performance of a control algorithm. In the device, a rotation part of a photoelectric encoder is sleeved and fixed on a rotating shaft of the single-shaft air-floating platform, and signals of the encoder are sent to a singlechip on the top surface of the single-shaft air-floating platform through a wireless communication module. The method comprises the following steps of: measuring an angular speed of the single-shaft air-floating platform by using the photoelectric encoder and sending the angular speed data to the singlechip on the top surface of the single-shaft air-floating platform through the wireless communication module. The simple simulation device and the simple ...

Control circuit of air-supporting rotating platform nozzle switch

The invention relates to a control circuit of an air flotation rotary table nozzle switch, in particular to a control circuit of a nozzle switch. The invention solves the problem that the damage of an operational amplifier and a peripheral circuit easily causes damage to an upper simulation system computer thereof in the existing control circuit of the air flotation rotary table nozzle. In the control circuit, a signal output end of an upper simulation system computer is connected with a signal input end of a CAN bus, a signal output end of which is connected with a signal input end of a singlechip; and a driving signal output end of the singlechip is connected with an input end of a limited current circuit, an output end of which is connected with a signal input end of a power amplifier.The control circuit is applicable to the control process of the movement of the air flotation rotary table.

Self-adaption on-board computer based on FPGA and method thereby for realizing dynamic allocation of internal resource

The invention discloses a self-adaption on-board computer based on FPGA and a method thereby for realizing dynamic allocation of internal resource, belonging to the technical field of space flight and aviation data processing, and solving the problem that the traditional reconfigurable on-board computer can not effectively manage reconfigurable FPGA resource. The on-board computer of the invention is realized by SRAM-type FPGA, the internal source of the SRAM-type FPGA comprises a main control unit and a reconfigurable unit array composed of n reconfigurable units with exactly same size, and the SRAM-type FPGA supports parts of reconfigurable technology. The method for realizing dynamic allocation of internal resource of the invention is characterized in that the main control unit configures the reconfigurable unit in the idle condition into a corresponding hardware circuit according to a hardware circuit needed by threads when the on-board computer starts a thread; when the thread ends ...

Desktop associated debugging device and method for small satellite electronic information processing system

The invention provides a desktop associated debugging device and method for a small satellite electronic information processing system, relating to a desktop associated debugging device and method for a satellite electronic information processing system, and aiming at solving the problems of high cost, low efficiency and complicated process in the conventional desktop associated debugging by adopting various sensors and execution mechanisms, and the problems that closed loop control of a control system cannot be performed and prototype functions and performances cannot be globally verified. In the device, a serial data output end of a simulator component is connected with a serial data input end of a prototype component, and a serial data input end of the simulator component is connected with a serial data input end of the prototype component; an analog data signal input end of the simulator component is connected with an analog data signal output end of the prototype component; and a data ...

Low-orbit aircraft based on aerodynamic attitude control and attitude control method thereof

The invention provides a low-orbit aircraft based on aerodynamic attitude control and an attitude control method thereof, relating to the low-orbit aircraft and the attitude control method thereof and solving the problems of high fuel consumption of the current low-orbit aircraft and the attitude control method thereof and short on-orbit service life of the aircraft. The low-orbit aircraft comprises an aircraft body, a pair of pitching-direction attitude control aerodynamic auxiliary boards, a pair of yawing-direction attitude control aerodynamic auxiliary boards, a first rotating mechanical arm, a second rotating mechanical arm, a third rotating mechanical arm and a fourth rotating mechanical arm. The attitude control method of the low-orbit aircraft comprises the following steps of: acquiring the current attitude angle and the target attitude angle of the low-orbit aircraft, obtaining a member to be deflexed and an angle through combining with aircraft attitude dynamics model and a kinematics ...

Distributed spacecraft ground artificial system and implementing method thereof

The invention discloses a distributed spacecraft ground simulation system and a method for realizing same, belonging to the technical field of space flight and aviation. The invention aims at solving the problems that the configuration of the simulation platform of a prior distributed spacecraft is solidified and the expandability is bad. The invention adopts a one-dimensional rotational base airfloated platform which is based on a plane two-dimensional parallel motion and is perpendicular to a parallel motion plane. By configuring a cooling air thrustor and a counteractive flywheel as an executing mechanism and configuring a high-precision optical fibre gyro, an x-axle accelerometer and a Y-axle accelerometer as a sensing component, the definition of a high-precision relative position and the standardization of an initiate posture can be realized by a high-precision local GPS positioning system, and other hardware systems can be configured according to different tasks, thereby forming ...

Finite state machine with radiating resistant function for reconfigurable satellite-loaded computer

The invention discloses a finite state machine with a radiating resistant function for a reconfigurable satellite-loaded computer and relates to the technical field of aerospace. The invention solves the problem of integral function invalidation of the reconfigurable satellite-loaded computer because the traditional reconfigurable satellite-loaded computer is short of resistance on space radiation. The finite state machine comprises an FPGA (Field Programmable Gate Array), a counter circuit and a timer circuit, wherein the FPGA comprises a selector, a register, a Hamming code checking circuit, a switch circuit and an in-chip dual-port RAM (Random Access Memory); the timer circuit is respectively connected with the counter circuit, the selector and the switch circuit; the counter circuit is also connected with the selector; the selector is also connected with the Hamming code checking circuit, the in-chip dual-port RAM and the register; the register is also connected with the in-chip dual-port ...

Time-variant computer and realizing method thereof

The invention relates to a time-varying computer based on a reorganization technology, and an on-board time-varying computer is formed by adopting the structures of a processor unit, a configuration unit and a radio frequency unit, the computer can realize the automatic switching function according to the mission of the satellite by a FPGA hardware program. The invention has strong processing capacity as the hardware program is adopted to realize the system function; meanwhile, the reorganization technology leads the time-varying computer to realize the fault tolerance function for each on-board computer, which avoids the influence on the satellite caused by the various hard wares of the system; at the same time, the time-varying computer can be upgraded on line.

Autonomous relative navigation method for multi-information fusion formation spacecrafts

The invention discloses an autonomous relative navigation method for multi-information fusion formation spacecrafts, belonging to the field of aviation and space and aiming at solving the problem that current relative navigation in a manner of GNSS plus inter-satellite link leads to no navigation redundancy information so that navigation precision is low. The method according to the invention comprises the steps: absolute navigation information of nodes of a spacecraft is obtained by utilizing a pulsar navigation system and a GNSS satellite navigation system; time synchronous information and distance information in relation to the nodes of other spacecrafts are obtained via a laser link system or a microwave link system and are used for the relative navigation of formation flying of the spacecrafts; the absolute navigation information completes inter-satellite information interaction with the nodes of other spacecrafts via the laser link system or the microwave link system in order toacquire ...

Sun vector measurement method and device thereof

Sun vector measurement method and device thereof

Autonomous relative navigation method for multi-information fusion formation spacecrafts

The invention discloses an autonomous relative navigation method for multi-information fusion formation spacecrafts, belonging to the field of aviation and space and aiming at solving the problem that current relative navigation in a manner of GNSS plus inter-satellite link leads to no navigation redundancy information so that navigation precision is low. The method according to the invention comprises the steps: absolute navigation information of nodes of a spacecraft is obtained by utilizing a pulsar navigation system and a GNSS satellite navigation system; time synchronous information and distance information in relation to the nodes of other spacecrafts are obtained via a laser link system or a microwave link system and are used for the relative navigation of formation flying of the spacecrafts; the absolute navigation information completes inter-satellite information interaction with the nodes of other spacecrafts via the laser link system or the microwave link system in order to acquire ...

Method and apparatus for simulating large thruster on spacecraft

The invention provides a method of a large-scale thrustor on a simulation spacecraft and a device thereof. The invention uses an air flotation three-axle table to simulate the body of a spacecraft. A control moment is formed by the push power generated by a plurality of small scale thrustors installed in different directions of the air flotation three-axle table. When the three-axle table works, namely when the spacecraft operates in orbit, the push power generated by small scale nozzles in all directions of the table drives the spacecraft to a target position according to a control instruction. In virtue of the design principle of equivalent scaling, the simulation of the control function of a large scale thrustor on a real spacecraft can be realized. The method is applicable to all situations that the air flotation tables are used for simulating the operation of the spacecraft in orbit and can lower the cost of ground simulation verification of the thrustor technology on the spacecraft ...

Distributed spacecraft ground artificial system and implementing method thereof

The invention discloses a distributed spacecraft ground simulation system and a method for realizing same, belonging to the technical field of space flight and aviation. The invention aims at solving the problems that the configuration of the simulation platform of a prior distributed spacecraft is solidified and the expandability is bad. The invention adopts a one-dimensional rotational base air floated platform which is based on a plane two-dimensional parallel motion and is perpendicular to a parallel motion plane. By configuring a cooling air thrustor and a counteractive flywheel as an executing mechanism and configuring a high-precision optical fibre gyro, an x-axle accelerometer and a Y-axle accelerometer as a sensing component, the definition of a high-precision relative position and the standardization of an initiate posture can be realized by a high-precision local GPS positioning system, and other hardware systems can be configured according to different tasks, thereby forming ...

Satellite attitude orienting system and method

The invention relates to a satellite attitude orientation system and a method thereof. A quaternion product unit inside the system adopts a hardware description language to design a hardware circuit, and a parallel calculation module is obtained; the parallel calculation module is utilized to carry out quaternion product operation of quaternion attitude parameters q<(1)> and q<(2)>, and a quaternion attitude parameter q' of a satellite reference system O mu v omega relative to a reference system Oxyz is obtained; and satellite attitude relative to a reference object can be determined according to q'. The method comprises: controlling data flow in each part of a control data path of a state controller; generating signal for loading, reading and shifting a register; and parallelly finishingquaternion product operation. The method can greatly increase the speed of quaternion operation in the orientation system, and can determine satellite attitude relative to a reference object at faster speed ...

Method and apparatus for simulating large thruster on spacecraft

The invention provides a method of a large-scale thrustor on a simulation spacecraft and a device thereof. The invention uses an air flotation three-axle table to simulate the body of a spacecraft. A control moment is formed by the push power generated by a plurality of small scale thrustors installed in different directions of the air flotation three-axle table. When the three-axle table works, namely when the spacecraft operates in orbit, the push power generated by small scale nozzles in all directions of the table drives the spacecraft to a target position according to a control instruction. In virtue of the design principle of equivalent scaling, the simulation of the control function of a large scale thrustor on a real spacecraft can be realized. The method is applicable to all situations that the air flotation tables are used for simulating the operation of the spacecraft in orbit and can lower the cost of ground simulation verification of the thrustor technology on the spacecraft ...

Laser protective cloth

Inter-satellite relative distance measurement device based on inter-satellite information exchange

An inter-satellite relative distance measurement device based on inter-satellite information exchange is disclosed, belonging to the field of aerospace application. The inventive aims at providing an inter-satellite information exchange-based inter-satellite relative distance measurement device which is simple in designed structure and capable of realizing relative navigation among a plurality of satellites. The invention uses an electric wire unit as a front end to accomplish the establishment of an inter-satellite link circuit with a field programmable gate array (FPGA) and a highly-integrated RF integrated nRF2401 RF chip; by means of the inter-satellite information exchange, the measurement of the inter-satellite relative distance is accomplished by utilizing time difference of record information transmitted among satellites, therefore the inter-satellite relative distance relationship can be calculated. The device is used for the measurement of the inter-satellite relative distance ...

Finite state machine with radiating resistant function for reconfigurable satellite-loaded computer

The invention discloses a finite state machine with a radiating resistant function for a reconfigurable satellite-loaded computer and relates to the technical field of aerospace. The invention solves the problem of integral function invalidation of the reconfigurable satellite-loaded computer because the traditional reconfigurable satellite-loaded computer is short of resistance on space radiation. The finite state machine comprises an FPGA (Field Programmable Gate Array), a counter circuit and a timer circuit, wherein the FPGA comprises a selector, a register, a Hamming code checking circuit, a switch circuit and an in-chip dual-port RAM (Random Access Memory); the timer circuit is respectively connected with the counter circuit, the selector and the switch circuit; the counter circuit is also connected with the selector; the selector is also connected with the Hamming code checking circuit, the in-chip dual-port RAM and the register; the register is also connected with the in-chip dual-port ...

Time-variant computer and realizing method thereof

The invention relates to a time-varying computer based on a reorganization technology, and an on-board time-varying computer is formed by adopting the structures of a processor unit, a configuration unit and a radio frequency unit, the computer can realize the automatic switching function according to the mission of the satellite by a FPGA hardware program. The invention has strong processing capacity as the hardware program is adopted to realize the system function; meanwhile, the reorganization technology leads the time-varying computer to realize the fault tolerance function for each on-board computer, which avoids the influence on the satellite caused by the various hard wares of the system; at the same time, the time-varying computer can be upgraded on line.

Method for producing disturbing torque to satellite using equivalent simulation of flexible accessory vibration by flywheel

The invention provides a method for generating interfering moment to a satellite by using flywheels to equivalently simulate the vibration of a flexible accessory, and relates to the method for generating the interfering moment to a satellite body by using the flywheels to equivalently simulate the vibration of the flexible accessory on a single-shaft air bearing table so as to solve the problemsthat the satellite simulation parameters are difficult to be equivalent to the real satellite parameters, and the environment has large difference from the environment of astrospace existing in the prior flexible satellite gesture semi-physical simulation method. The method utilizes the single-shaft air bearing table to simulate a spacecraft body, the control moment is provided by one flywheel arranged on the air bearing single-shaft table, and flexible interfering moment is equivalently provided by another two flywheels. When the single-shaft air bearing table simulates the spacecraft to run on ...

Method for producing disturbing torque to satellite using equivalent simulation of flexible accessory vibration by flywheel

The invention provides a method for generating interfering moment to a satellite by using flywheels to equivalently simulate the vibration of a flexible accessory, and relates to the method for generating the interfering moment to a satellite body by using the flywheels to equivalently simulate the vibration of the flexible accessory on a single-shaft air bearing table so as to solve the problems that the satellite simulation parameters are difficult to be equivalent to the real satellite parameters, and the environment has large difference from the environment of astrospace existing in the prior flexible satellite gesture semi-physical simulation method. The method utilizes the single-shaft air bearing table to simulate a spacecraft body, the control moment is provided by one flywheel arranged on the air bearing single-shaft table, and flexible interfering moment is equivalently provided by another two flywheels. When the single-shaft air bearing table simulates the spacecraft to run on ...

On-line restoration method of permanent fault circuit of reconfigurable satellite-borne computer

The invention provides an on-line restoration method of a permanent fault circuit of a reconfigurable satellite-borne computer, which relates to the technical fields of space flight and aviation and solves the problem that irreparable damage generated by an FPGA circuit in a traditional reconfigurable satellite-borne computer under the influence of space radiation causes a permanent circuit fault directly. The on-line restoration method comprises the following steps of: firstly, determining an FPGA circuit generating a permanent circuit fault by a radiation hardening processor, then starting using the other FPGA circuit to work by the radiation hardening processor and finally, carrying out on-line restoration on the FPGA circuit generating the permanent circuit fault by the radiation hardening processor. The invention is suitable for reconfigurable satellite-borne computers.

Inter-satellite relative distance measurement device based on inter-satellite information exchange

An inter-satellite relative distance measurement device based on inter-satellite information exchange is disclosed, belonging to the field of aerospace application. The inventive aims at providing an inter-satellite information exchange-based inter-satellite relative distance measurement device which is simple in designed structure and capable of realizing relative navigation among a plurality ofsatellites. The invention uses an electric wire unit as a front end to accomplish the establishment of an inter-satellite link circuit with a field programmable gate array (FPGA) and a highly-integrated RF integrated nRF2401 RF chip; by means of the inter-satellite information exchange, the measurement of the inter-satellite relative distance is accomplished by utilizing time difference of recordinformation transmitted among satellites, therefore the inter-satellite relative distance relationship can be calculated. The device is used for the measurement of the inter-satellite relative distance.

Multi-core onboard spacecraft computer based on FPGA

The invention relates to a multi-core satellite-bone computer, belonging to the data processing technical field of aerospace and aiming at solving the problem of slow processing speed of the satellite-bone computer by adopting an ASIC software realization mode. The satellite-bone computer comprises an FPGA based on an SRAM, n PROMS, n SRAMS, an anti-fuse FPGA and a configuration NOR type flash memory, wherein the FPGA based on the SRAM forms a multi-core structure with n processors, the anti-fuse FPGA comprises a read-back brush write interface circuit, a monitoring circuit and a control circuit, the monitoring circuit monitors the health state of the n processors, if an abnormal part needs reconstruction, the read-back brush write interface circuit reads the configuration file of the FPGA based on the SRAM at set speed, compares the configuration file of the FPGA with an original configuration file, and reconstructs the error parts if different. The multi-core satellite-bone computercan ...

Wireless communication module and wireless communication satellite using module

The invention discloses a wireless communication module and a wireless communication satellite using the module, relates to a wireless communication module and a wireless communication satellite, and solves the problems that the conventional satellites have complex structure, poor reliability and poor safety and are not favorable for tests. In the wireless communication module, a radio frequency antenna is connected with a radio frequency signal transmitting/receiving end of a radio frequency chip circuit; a signal end of the radio frequency chip circuit is connected with a signal end of a microcontroller; and an external data acquisition and control signal end of the microcontroller is a baseband data input/output end of the wireless communication module. In the wireless communication satellite, a power supply provides working power for a measurement and control system, a satellite management system, an attitude and orbit control system and an effective load management and control system ...

Simple simulation device and simulation method applied to star sensor of single-shaft air-floating platform

The invention relates to a simple simulation device and a simple simulation method applied to a star sensor of a single-shaft air-floating platform, which solve the problems that the star sensor in the semi-physical simulation of a conventional ground spacecraft cannot access a simulation system and then cannot test the performance of a control algorithm. In the device, a rotation part of a photoelectric encoder is sleeved and fixed on a rotating shaft of the single-shaft air-floating platform, and signals of the encoder are sent to a singlechip on the top surface of the single-shaft air-floating platform through a wireless communication module. The method comprises the following steps of: measuring an angular speed of the single-shaft air-floating platform by using the photoelectric encoder and sending the angular speed data to the singlechip on the top surface of the single-shaft air-floating platform through the wireless communication module. The simple simulation device and the simple ...