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

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 provides a FPGA-based embedded cubic star service computer, comprising a processing chip, the processing chip is integrated with an FPGA hard core, an FPGA logic unit, and a CPU core; Each sub-system communicates; the FPGA logic unit is used to control the peripheral circuit, and at the same time correct the local time of the star service of the cube star; the CPU core is used to realize the whole star control algorithm for the cube star, Whole-star data management, attitude control algorithm implementation, control command distribution and load data management. The invention has flexible use, optimized performance, high integration, low cost and high reliability.

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.

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 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.