36results about How to "Meet the needs of different tasks" patented technology

The invention discloses a modular reconfigurable robot, and belongs to the technical field of articulated robots. The modular reconfigurable robot comprises an upper computer and a robot, wherein the robot is connected with a controller area network (CAN) communication interface card of the upper computer through a CAN bus. The modular reconfigurable robot is characterized in that: the robot comprises a base module, a clamping jaw module and a plurality of joint modules and connecting rod modules alternately connected between the base module and the clamping jaw module, and the modules are combined into multiple structural robots of 2 to 7 degrees of freedom, wherein the base module is connected with the joint modules, the clamping jaw module is connected with the connecting rod modules, and a power / signal bus for electric connection is arranged in each module. Plug D-type connectors are adopted at electric connection interfaces of all the modules; and flange structures are adopted at mechanical interfaces of all the modules, so the robot is simply assembled and disassembled and easily positioned. The assembled robot has no exposed electric wire, so the electric wire winding problem is not produced when the robot moves. Mechanical and electric limits are arranged in the joint modules, so the use safety of the robot is improved.

The invention provides an embedded cubic star task computer based on an FPGA (Field Programmable Gate Array). The computer comprises a processing chip, wherein the processing chip is integrated with an FPGA hard core, an FPGA logic unit and a CPU (Central Processing Unit) inner core; the FPGA hard core is used for communicating with a peripheral circuit and various subsystems of a cubic star; the FPGA logic unit is used for controlling the peripheral circuit and meanwhile timing the star task local time of the cubic star; the CPU inner core is used for performing whole star control algorithm implementation, whole star data management, gesture control algorithm implementation, control command dispatching and load data management on the cubic star. The embedded cubic star task computer has the advantages of flexibility in use, optimized performance, high integration level, low cost and high reliability.

The invention discloses a task distribution and route planning method of an unmanned aerial vehicle. The route planning is divided into two steps. The first step is that a flying route of the unmannedaerial vehicle from a base station to every key patrolling zone is acquired through Dijkstra algorithm; the second step is that the zone where the unmanned aerial vehicle cannot pass is set as a barrier for considering about the altitude factor; an ant colony algorithm is applied to focus on inspecting the longest distance of flying in the key inspection zone within specified four hours under thecondition of returning to a base station and avoiding the barrier. The method can meet different task demands; firstly, the method can rapidly learn about the disaster area, avoid barrier while fly from the base station to a target zone within the shortest time, and inspect as more as ranges during the duration of flight, so as to take it as the target to plan the flight route of the unmanned aerial vehicle; secondly, the patrolling tasks and the flight route are reasonably distributed for fully using the resource in the presence of multiple unmanned aerial vehicle base stations; thus the utilization rate of the unmanned aerial vehicle in the base station is maximized.

The invention relates to a coaxial double-rotor ducted aircraft, which solves the problems of poor high-speed flight capability and complex structure of ordinary rotorcraft. The upper bracket and the lower bracket are connected by a support plate to form a whole machine bracket, and have an airfoil duct body Around the support, the landing gear is installed on the periphery of the lower support, the motor power supply is installed on the upper part of the upper support, and the coaxial motor composed of two motors of the same type is installed in the center of the upper support. The propeller is fixed on the propeller shaft of the motor. The two propellers are of the same type. The direction of rotation of the propellers is opposite, the lower bracket is equipped with the lower central body, the upper layer of the lower central body is equipped with the attitude reference system, the middle layer is equipped with the power supply of the flight control system, the lower layer is equipped with the flight control board, and the inner circumference of the lower bracket is equidistantly installed. The steering gear is connected to the control panel through the control panel linkage. The invention has hovering, low-speed and high-speed flight capabilities, can take off and land vertically, has strong adaptability, good concealment, compact structure and wide application range.

The invention provides a multi-joint mechanical arm mechanism. Two sub-arms are connected through a specific joint, and every two adjacent joints have incompletely same structures. Besides arms, a connecting rod is connected among every two joints, and the connecting rod, the sub-arms and the joints thereof form a parallelogram. In addition, the joints and the arms are connected through a cylinder. Some section of the cylinder is driven to extend out to a proper position, thus the section of the sub-arm can unbend, otherwise, the section of the sub-arm is driven to fold. As required, the invention can arbitrarily deform the mechanical arm so as to satisfy the requirements of different operation tasks. The mechanism can realize the over-length requirement of the arm, is convenient to fold and greatly reduces the transportation and storage space. In addition, the mechanism can get rid of length restriction based on multiple sections of telescopic cylinders, and the joints and folding arms can be increased and decreased according to requirements, thereby being convenient for the flexibly design of long arms and super long arms.

The invention relates to the field of pilotless helicopters, especially to a modularized pilotless helicopter for task loads. The total design of the pilotless helicopter is carried out by taking task loads as a constituent part of the pilotless helicopter. The pilotless helicopter is divided into an upper part flight platform module (1) and a lower part task load module (2); wherein the flight platform module (1) comprises regular basic components of a pilotless helicopter, the regular basic components consisting of a fuselage (101), a rotor system (102), a flight control system (103), a power system (104), a electric power system (105), cables and interfaces (106); the task load module (2) mainly consists of a load cabin (201); and the two modules are rigorous in anastomosis and firm in connection and form an integral pilotless helicopter. The problems that a conventional pilotless helicopter with a limit capacity in a singularity shape cannot be suitable for various kinds of load devices in various sizes and shapes is solved by the modularized pilotless helicopter for task loads of the invention, and the flexibility of the task load integrated usage and the multitask execution capability of the pilotless helicopter are both improved.

The invention discloses a power density adjustable film reflecting and condensing space solar energy collecting station, which comprises a spacecraft platform, an optical system and a light path adjusting mechanism, wherein the optical system comprises a main condenser, an auxiliary condenser and a plane mirror; the main condenser and the auxiliary condenser are arranged in opposite directions, optical axes of the main condenser and the auxiliary condenser are overlapped, and a normal distance between the main condenser and the auxiliary condenser is adjusted through the light path adjusting mechanism to change the power density of output light beams; the angle of the plane mirror is adjusted through the light path adjusting mechanism to change the direction of the output light beams; sunlight is condensed and reflected to the auxiliary condenser through the main condenser, the reflected light rays are condensed and reflected to the plane mirror through the auxiliary condenser, and the light beams are reflected to a target through the plane mirror.

The invention provides a distributed high-precision laser online measurement system. A main / backup laser device acts as an emitting light source. Emitting laser is divided into multipath emitting light beams through an optical beam combiner, an optical circulator and an optical beam splitter. The number of split light paths of the emitting light beams is further increased by an optical switch array, and the optical switches can perform time sequence switching on emergent light paths through the control of the system. Each path of emergent laser is corresponding to one optical transmit-receive antenna so as to be corresponding to one cooperative target body. Laser returned by the cooperative target returns to the optical circulator through the light paths and enters a photoelectric detector. Echo phase calculation is performed by a signal processing system after photoelectric conversion of the photoelectric detector so that accurate distance information of a target dot matrix can be obtained. In-orbit real-time deformation measurement is performed on satellite antennas and other large deployable mechanisms, and imaging resolution of the large antennas and the calculated image quality can be enhanced by measurement of the antenna surface.

The invention provides a virtual constellation-based resource alliance construction method for a cooperative task, and relates to the field of satellite resource organization. The method comprises thesteps that when a virtual constellation management and control system receives a to-be-processed task, a plurality of satellites are selected according to demand information of the to-be-processed task to form a candidate satellite set, one satellite is randomly selected from the candidate satellite set to serve as a satellite leader, and the to-be-processed task is sent to the satellite leader;When the satellite leader receives the to-be-processed task, the pursuit interest degree, reliability, timeliness and income value of each satellite in the candidate satellite set are calculated for the to-be-processed task; an objective function is determined; And a satellite alliance corresponding to the to-be-processed task is determined according to the objective function, and executing the to-be-processed task by utilizing the satellite alliance. According to the invention, satellite resources can be effectively organized and optimized.

The invention discloses a hydraulic-electric combined space thruster, comprising a combustion chamber, a catalyst, an insulator, an anode, a sprayer nozzle, a permanent magnet ring and a power supplysystem. Catalyst particles are filled in a combustion chamber. A circular through hole is formed between two end faces of the insulator, and the insulator is installed in the combustion chamber and ison downstream of the catalyst (along the flow direction of a propellant, the same below). Geometric profile of the anode is the same with that of the insulator, and the anode is installed in the combustion chamber and is on downstream of the insulator. The sprayer nozzle is connected with the tail of the combustion chamber. The permanent magnet ring is nested on the tail end outside the combustion chamber. The positive pole of the power supply system is connected with the anode, and a negative pole is connected with the catalyst. A liquid rocket engine and a plasma rocket engine are integrated in one hydraulic-electric combined space thruster, so that one engine has two working modes. When an aircraft executes low orbit tasks, the aircraft works by using a combustion propellant (chemicalenergy of the propellant is converted into kinetic energy). When the aircraft performs high-orbit or deep-space exploration missions, the aircraft uses plasma propulsion to work (converts kinetic energy of a power source into kinetic energy), so that one thruster can meet different mission requirements of the aircraft, thereby reducing total mass of a spacecraft.

The invention discloses a design of a low-cost planar phased-array antenna for low-orbit satellite communication and a method for realizing phased-array scanning by using the low-cost planar phased-array antenna. The method mainly comprises the following steps: S1, setting Nx * Ny array elements for a phased-array antenna, correspondingly providing Nx * Ny feeding points, and regularly arranging the Nx * Ny feeding points in a rectangular grid shape: the distance between two adjacent feeding points in the horizontal direction is dx, and the distance between two adjacent feeding points in the vertical direction is dy; S2, controlling the on-off of the PIN diode to feed each array element in different directions to realize the equivalent space rotation of the array element; and S3, feeding the Nx * Ny array elements, and controlling on / off of PIN diodes on the antenna units through direct current to obtain different phase distributions so as to realize two-dimensional scanning of the phased array.

The present application relates to a data resource, disclosing a data synchronization generation method, an apparatus, a computer device and a storage medium, wherein, the data synchronization generation method comprises the following steps: reading a table structure of a preconfigured configuration table synchronizing the data of the relational database to a large data platform in a relational database to obtain configuration information of the configuration table; Generating scheduling tasks, scripts and table building statements corresponding to the big data platform according to the configuration information; The scheduling task, the script and the table building statement are respectively transmitted to the designated position of the big data platform to schedule the designated data of the relational database to the big data platform. Sqoop data synchronization automatic generation tool is developed, which can automatically generate Sqoop data synchronization script files and build table statements, directly deploy (hang on another platform), and control the synchronization of script files through the platform. The script running platform is unified and centralized, which is convenient for operators to manage all the script running conditions.

The invention relates to an automatic magnetic fingerprint brush. The brush includes a handle and a brush head internally provided with a permanent magnet and a connecting base; the permanent magnet is fixed to the lower portion of the connecting base; the inner side wall of the brush head is evenly provided with two track grooves, the circumferential surface of the connecting base is provided with sliding blocks corresponding to the two track grooves in a one-to-one mode, and the sliding blocks are connected to the track grooves in a sliding mode; a spring is installed between the bottom of the brush head and the connecting base; the sliding blocks are clamped to lower locating points of the track grooves, and the brush head is used for attracting magnetic powder; the sliding blocks detach from the lower locating points and are reset to high locating points under the effect of the spring, and then the brush head releases the magnetic powder; the bottom of the handle is fixedly provided with a connecting shaft made of ferromagnetic metal; a first sleeve hole is formed in the portion corresponding to the permanent magnet and above the connecting base, and a connecting shaft is sleeved in the first sleeve hole, so that under the effect of the magnetic attraction force of the permanent magnet, the connection between the brush head and the handle is achieved. The automatic magneticfingerprint brush is small, exquisite, light and portable in structure, convenient to use and capable of reducing load of surveyors and improving the survey efficiency.

The invention discloses a light concentrating multipurpose satellite system with adjustable power density. The light concentrating multipurpose satellite system comprises a spacecraft platform, an optical system, an optical path adjusting mechanism and a direction control mechanism, wherein the optical system comprises a main collecting lens, an auxiliary collecting lens and a plane mirror; the auxiliary collecting lens is located at the back of the main collecting lens and is overlapped with an optical axis; the normal distance between the main collecting lens and the auxiliary collecting lens is adjusted by the optical path adjusting mechanism, and the power density of output light beams is changed; the angle of the plane mirror is adjusted by the direction control mechanism, and the light beams which are reflected by the plane mirror aim at a target; sunlight is subjected to transmission by the main collecting lens to be concentrated to the auxiliary collecting lens, the light beams are concentrated by the auxiliary collecting lens and then are reflected to the plane mirror, and the light beams are reflected to the target by the plane mirror.

The invention belongs to the technical field of underwater robots, and particularly relates to a flying airfoil towfish driven by ocean currents. In the absence of a buoyancy adjusting device, an anchoring base and an anchor chain are fixed in a certain area, the lifting action force of the ocean currents is changed by adjusting the attack angle between a wing body and the ocean currents, and three different motion effects of floating up, diving down and suspension are realized. The flying airfoil towfish driven by the ocean currents does not rely on a water surface communication buoy, can emerge from the water periodically and uses a hydrofoil antenna mast for communication and data transmission. A flow guide housing in a blended wing body form is adopted, the lift-drag ratio of the flying airfoil towfish can be greatly improved, and it is ensured that the flying airfoil towfish can still operate normally under the condition of small ocean currents. Meanwhile, the flying airfoil housing provides a large volume space and can carry more mission sensors to meet different mission requirements. The flying airfoil towfish driven by ocean currents has the characteristics of low energy consumption, large effective payloads, high security and good concealment, and can be used for monitoring the ocean environment in the area for a long time.

A two-layer unfoldable antenna mechanism driven by a torsion spring based on a shear type mechanism includes a torsion spring assembly and a shear type mechanism, the torsion spring assembly includesa torsion spring support, torsion springs, pins and rigid hinges, two coaxial through holes are respectively arranged on opposite two supporting plates of the torsion spring support, A pin shaft is installed in each pair of through holes, A torsion spring and a rigid hinge are respectively nested on the pin shaft, and the other end of the rigid hinge is fixedly connected with the connecting rod onthe scissors-type deployable unit. The scissors-type mechanism comprises a scissors-type deployable unit and a support frame, and the scissors-type mechanism is driven by the torsion spring to drivethe unfolding or folding motion of the scissors-type mechanism, thereby realizing the unfolding and folding behavior of the whole mechanism. As that torsion spring is used as the drive source, the invention realizes the motor-free driving and unfolding, so that the unfolding response of the mechanism is rapid, and the overall weight of the mechanism is reduce at the same time. The invention has the characteristics of simple driving, light structure quality, large space folding ratio, expansibility of the unit, and high practicability.

The invention discloses an electro-chemical hybrid power space thruster which comprises a shell, an insulating heat-insulating sleeve, a spring, a low-voltage cathode, an electronic control solid propellant, a low-voltage anode, an insulating plate, a high-voltage anode, an electric propulsion propellant, a high-voltage cathode, an insulating sleeve and a fixed contact pin. The electronic control solid propellant is used for replacing a traditional solid chemical propellant, and multiple times of ignition and flameout of the solid propellant and thrust adjusting operation are achieved. A traditional solid chemical thruster is improved, the traditional solid chemical thruster and a pulse plasma thruster are integrated into a set of electro-chemical hybrid poewr space thruster, and the requirements for large thrust and high specific impulse of space propulsion are met; and when the thruster combusts the electronic control solid propellant to work, products generated by combustion can be accelerated by the action of an electric field between the high-voltage anode and the high-voltage cathode, and thrust and specific impulse during electrochemical propulsion are increased.

The invention relates to an unmanned aerial vehicle path and action planning algorithm for indoor positioning information collection, and belongs to the field of Internet of Things. Actions and pathsare planned for an unmanned aerial vehicle carrying signal collection equipment (wireless network card), and channel state information (CSI) signals in a three-dimensional space are detected, so thatthe invention is used for establishing an indoor positioning information fingerprint map. Compared with manual CSI signal detection, the unmanned aerial vehicle reduces signal disturbance, and path and action planning avoids indoor collision of the unmanned aerial vehicle and greatly reduces energy consumption. After an indoor environment, unmanned aerial vehicle motion and energy are modeled, a planning problem is converted into a generalized traveling salesman problem (GTSP), so that a GLNS solver is used for optimization.

The invention discloses a task distribution and route planning method of an unmanned aerial vehicle. The route planning is divided into two steps. The first step is that a flying route of the unmannedaerial vehicle from a base station to every key patrolling zone is acquired through Dijkstra algorithm; the second step is that the zone where the unmanned aerial vehicle cannot pass is set as a barrier for considering about the altitude factor; an ant colony algorithm is applied to focus on inspecting the longest distance of flying in the key inspection zone within specified four hours under thecondition of returning to a base station and avoiding the barrier. The method can meet different task demands; firstly, the method can rapidly learn about the disaster area, avoid barrier while fly from the base station to a target zone within the shortest time, and inspect as more as ranges during the duration of flight, so as to take it as the target to plan the flight route of the unmanned aerial vehicle; secondly, the patrolling tasks and the flight route are reasonably distributed for fully using the resource in the presence of multiple unmanned aerial vehicle base stations; thus the utilization rate of the unmanned aerial vehicle in the base station is maximized.

The invention discloses a method and a device for generating an identification code, electronic equipment and a storage medium. The method comprises the steps of: receiving an identification code generation request which comprises a product name and a product type of a target product; generating a product identification code corresponding to the target product according to the identification codegeneration request, wherein the product identification code comprises a first field, a second field, a third field, a fourth field and a fifth field, the first field is used for indicating a manufacturer of the target product, the second field is used for indicating a product type of the target product, the third field is used for indicating a production date of the target product, the fourth field is used for indicating a production place of the target product, and the fifth field is used for indicating a production sequence of the target product in the same type of products within the production date; and storing an association relationship between the product name and the product identification code in a product information table.

The invention discloses a liquid-electric combination space thruster, which comprises a combustion chamber, a catalyst, an insulator, an anode, a nozzle, a permanent magnet ring and a power supply system. The catalyst particles are filled inside the combustion chamber; a circular through hole is opened between the two end faces of the insulator, and installed in the combustion chamber, located downstream of the catalyst (along the flow direction of the propellant, the same below); the geometric shape of the anode and the insulator The same, and installed in the combustion chamber, located downstream of the insulator; the nozzle is connected to the tail of the combustion chamber; the permanent magnet ring is nested at the outer tail of the combustion chamber; the positive pole of the power supply system is connected to the anode, and the negative pole is connected to the catalyst . The present invention integrates the liquid rocket engine and the plasma rocket engine into a liquid-electric combined space thruster, so that one engine has two working modes, and the aircraft uses the mode of burning propellant to work when performing low-orbit missions (the propulsion The chemical energy of the agent is converted into kinetic energy), and the aircraft uses plasma propulsion when performing high-orbit or deep-space exploration missions (converting the kinetic energy of the power supply into kinetic energy), so that one thruster can meet the needs of different missions of the aircraft, thereby reducing the total mass of the spacecraft.

The invention provides a three-mold symplasm spatial nuclear propulsion system based on metal hydride. The system comprises a spatial nuclear reactor, a metal hydride storage and supply subsystem, a hydrogen nuclear heat propulsion subsystem, a metal steam nuclear heat propulsion subsystem and a high-power nuclear power propulsion subsystem, wherein the spatial nuclear reactor is used for respectively supplying heat to the metal hydride storage and supply subsystem, the hydrogen nuclear heat propulsion subsystem, the metal steam nuclear heat propulsion subsystem and the high-power nuclear power propulsion subsystem by virtue of internal heating pipes, and the metal hydride storage and supply subsystem is connected with the hydrogen nuclear heat propulsion subsystem, the metal steam nuclearheat propulsion subsystem and the high-power nuclear power propulsion subsystem, respectively through a pipeline I, a pipeline II and a pipeline III. According to the three-mold symplasm spatial nuclear propulsion system based on the metal hydride, two propulsion mediums are acquired through the decomposition of single metal hydride with relatively good thermal stability by virtue of the heat energy of the spatial nuclear reactor, and three propulsion modes are formed.

The invention discloses a dual-power layout mode eight-propeller remote control unmanned submersible which comprises a machine body, four horizontal propellers, two vertical propellers and two adjustable propellers, and the four horizontal propellers, the two vertical propellers and the two adjustable propellers are fixed to the machine body. The two adjustable propellers and the two side plates are arranged in a one-to-one correspondence mode, and the adjustable propellers are fixed to the side plates in the vertical direction and the transverse direction in an adjustable mode. A dual-power layout is adopted: a 4 + 4 mode and a 6 + 2 mode are adopted, and can be switched within one minute, so that the device is suitable for two application directions, and different task requirements during each time of going out of sea are met; the 4 + 4 mode can ensure sufficient load and posture adjusting capability; and the 6 + 2 mode can greatly improve the operation speed.

The invention discloses a light concentrating multipurpose satellite system with adjustable power density. The light concentrating multipurpose satellite system comprises a spacecraft platform, an optical system, an optical path adjusting mechanism and a direction control mechanism, wherein the optical system comprises a main collecting lens, an auxiliary collecting lens and a plane mirror; the auxiliary collecting lens is located at the back of the main collecting lens and is overlapped with an optical axis; the normal distance between the main collecting lens and the auxiliary collecting lens is adjusted by the optical path adjusting mechanism, and the power density of output light beams is changed; the angle of the plane mirror is adjusted by the direction control mechanism, and the light beams which are reflected by the plane mirror aim at a target; sunlight is subjected to transmission by the main collecting lens to be concentrated to the auxiliary collecting lens, the light beams are concentrated by the auxiliary collecting lens and then are reflected to the plane mirror, and the light beams are reflected to the target by the plane mirror.

The invention discloses a multi-constraint guidance method containing the normal acceleration derivative for a glide phase of an air-launched cruise missile. The multi-constraint guidance method specifically comprises the steps that firstly, missile aerodynamic parameters are determined, and parameters of an atmosphere model are established; secondly, a missile motion equation set is established according to the missile aerodynamic parameters and the parameters of the atmosphere model; thirdly, linear processing is conducted on the missile motion equation set; fourthly, a normal acceleration derivative equation is added in the equation set which is linearly processed, and an analytical algorithm equation set is obtained; fifthly, the tail end constraint and the path constraint which need to be met through the glide phase of a trajectory are determined; sixthly, the optimal controlled variable u is determined according to the analytical algorithm equation set and the optical control index function; and seventhly, an analytical guidance law is obtained by solving the optimal controlled variable u, and thus the glide phase of the trajectory of the missile meets the tail end constraint and the path constraint. The multi-constraint guidance method has the advantages that the constraints of the trajectory inclination angle, speed, normal acceleration and normal acceleration first derivative are met while the effect that the missile reaches the regulated tail end height is guaranteed, and the flying quality of the missile is improved.

Disclosed are a negative-pressure adsorption type wall-climbing robot and a system thereof. Through the negative-pressure adsorption type wall-climbing robot and the system thereof, the technical problems of many limits to the usage range and usage environment, poor universality, difficult maintenance, high function extension and technology upgrading difficulty and the like of an existing wall-climbing robot are mainly solved. According to the main points of the technical scheme, the negative-pressure adsorption type wall-climbing robot comprises a power negative-pressure adsorption type wall-climbing robot body (1), an unpowered negative-pressure adsorption type wall-climbing robot body (2) and a system control device. The negative-pressure adsorption type wall-climbing robot and the system thereof are mainly applied to robot work in various complex environments.

The invention discloses a modular reconfigurable robot, and belongs to the technical field of articulated robots. The modular reconfigurable robot comprises an upper computer and a robot, wherein the robot is connected with a controller area network (CAN) communication interface card of the upper computer through a CAN bus. The modular reconfigurable robot is characterized in that: the robot comprises a base module, a clamping jaw module and a plurality of joint modules and connecting rod modules alternately connected between the base module and the clamping jaw module, and the modules are combined into multiple structural robots of 2 to 7 degrees of freedom, wherein the base module is connected with the joint modules, the clamping jaw module is connected with the connecting rod modules, and a power / signal bus for electric connection is arranged in each module. Plug D-type connectors are adopted at electric connection interfaces of all the modules; and flange structures are adopted atmechanical interfaces of all the modules, so the robot is simply assembled and disassembled and easily positioned. The assembled robot has no exposed electric wire, so the electric wire winding problem is not produced when the robot moves. Mechanical and electric limits are arranged in the joint modules, so the use safety of the robot is improved.

The invention provides a three-mold symplasm spatial nuclear propulsion system based on metal hydride. The system comprises a spatial nuclear reactor, a metal hydride storage and supply subsystem, a hydrogen nuclear heat propulsion subsystem, a metal steam nuclear heat propulsion subsystem and a high-power nuclear power propulsion subsystem, wherein the spatial nuclear reactor is used for respectively supplying heat to the metal hydride storage and supply subsystem, the hydrogen nuclear heat propulsion subsystem, the metal steam nuclear heat propulsion subsystem and the high-power nuclear power propulsion subsystem by virtue of internal heating pipes, and the metal hydride storage and supply subsystem is connected with the hydrogen nuclear heat propulsion subsystem, the metal steam nuclearheat propulsion subsystem and the high-power nuclear power propulsion subsystem, respectively through a pipeline I, a pipeline II and a pipeline III. According to the three-mold symplasm spatial nuclear propulsion system based on the metal hydride, two propulsion mediums are acquired through the decomposition of single metal hydride with relatively good thermal stability by virtue of the heat energy of the spatial nuclear reactor, and three propulsion modes are formed.