67results about How to "Satisfy mission requirements" patented technology

The invention discloses an underwater working robot which is characterized by mainly comprising a vehicle body module, a manipulator module or/and an underwater camera module, a functional component module and a control module, wherein the modules are completely isolated mechanically and electrically; the vehicle body module mainly comprises a six-wheel and six-drive sealing vehicle body, a vehicle body direct current servo motor, a vehicle body motor driver, a vehicle body underwater ultrasonic sensor, a vehicle body temperature pressure sensor, an underwater lighting lamp, a vehicle body waterproof plug, a vehicle body inflating valve and a vehicle body anti-radiation lead plate; the manipulator module mainly comprises a base, a waist part, a large arm, a small arm and a tail end executer; the base, the waist part, the large arm and the small arm are connected with one another through hollow joints; air is filled into a manipulator, and wires are arranged in the manipulator; the underwater camera module mainly comprises an underwater camera, an underwater camera lighting lamp and a bidimensional tripod; the functional component module mainly comprises a storage box, an underwater dust remover and an underwater cutter; and the control module mainly comprises a main control console and a hand-control box.

The invention relates to a combination type high-altitude precise aerial delivery system, which is composed of a controllable parafoil aircraft assembly, a detachable power assembly and a detachable round parachute assembly. After being delivered in high altitude, the system is controlled autonomously and lands on a destination safely and precisely. When both the flying environment and the landing environment are good, the controllable parafoil aircraft assembly is only used to execute a task, thus, the flying weight of the system is lightened, and the system is simplified. The controllable parafoil aircraft assembly and the detachable power assembly are combined, thus, the system can be applied to a severe flying environment; furthermore, the flying delivery distance can also be prolonged. The controllable parafoil aircraft assembly and the detachable round parachute assembly are combined, thus, the round parachute can be opened when the system reaches a low-altitude airspace of a landing point to realize ease landing, and, the system can be applied to a severe landing environment. The controllable parafoil aircraft assembly, the detachable power assembly and the detachable round parachute assembly are combined, thus, the system can be applied to the severe flying environment; the flying delivery distance can be prolonged; furthermore, the system can be applied to the sever landing environment to realize the ease landing. The system disclosed by the invention is multifunctional and wide in application range.

The invention discloses an electric pump conveying system for a solid-liquid rocket engine. The electric pump conveying system comprises a high-pressure gas bottle and a storage box. The high-pressure gas bottle is connected with a storage box through a first pipeline. The storage box is connected with a thrust chamber through a second pipeline. A pressurizing one-way valve, pore plates, gas path high-speed electromagnetic valves, a storage box exhaust hand valve and a safety valve are mounted on the first pipeline. A filling-discharging hand valve, a diaphragm valve, a pump, a flow adjusting valve and a liquid path high-speed electromagnetic valve are mounted on the second pipeline, wherein the pump is connected with a motor. By controlling opening and closing of the gas path electromagnetic valves, the pressure of the storage box is adjusted to meet the task requirement; when the pressure of the storage box exceeds the break valve of the diaphragm valve, the diaphragm valve breaks; and oxidizing agents in the storage box are pressurized through the pump driven by the motor after passing through the diaphragm valve, and then the flow of the oxidizing agents is controlled through the flow adjusting valve, after the liquid path high-speed electromagnetic valve is opened, the oxidizing agents are supplied to the thrust chamber according to the flow and pressure of task requirements. The electric pump conveying system is especially suitable for a solid-liquid rocket engine on a small carrier rocket.

The invention discloses a shooting guiding type dynamic detection system for a wind power blade defect of an unmanned aerial vehicle. The detection system comprises a global blade motion measurement system, a local unmanned aerial vehicle station blade damage detection system, an information processing analysis and control system, and a field comprehensive support and support system. In addition,the invention also discloses a detection method based on the system. Camera calibration is carried out; the global measurement system collects an image of the rotating blade, full-field displacement and strain information of the blade is obtained, and the contour of the rotating blade is extracted; short-distance local observation of the unmanned aerial vehicle is controlled and planned, high-resolution images of local areas of interests of the blade at different positions under different stress states are obtained; and artificial or semi-automatic fault detection analysis is performed according to the displacement of the feature points on the blade and image changes. The detection process is stable; the high-precision detection of the global and local surfaces of the large-scale wind power blade is realized; the detection efficiency is high; the functions are diversified; the system is easy to control; and lots of manpower is saved.

The invention discloses a distance zero-value calibration method and system based on integration of measurement, control, and data transmission. The method comprises: determining a reset pulse per second according to a system clock, a spread spectrum pseudo code frequencies of a non-coherent spread spectrum system, and a symbol rate of a measurement, control, and data transmission integration system after high-speed transmission frame coding; on the basis of the reset pulse per second, determining an uplink time enabling pulse of the non-coherent spread spectrum system and an uplink time enabling pulse of a high-speed transmission frame; and carrying out accurate alignment on the uplink time enabling pulse of the non-coherent spread spectrum system and the uplink time enabling pulse of thehigh-speed transmission frame to enable transmitting delays of ground station equipment to be equal, and realizing distance zero-value separation of a responder by using a zero calibration frequencyconverter. Therefore, a problem that the distance zero values of the responder can not be separated directly when the uplink and downlink radio-frequency characteristics are different is solved; and the effective, simplified, and reliable task requirement of the distance zero value separation method is met.

The invention discloses an airport flight resource and airplane scheduling method and scheduling system. The scheduling system records the use situation of transport vehicles, maintenance points, take-off and landing runways and other resources and the position and the state of airplanes and records and updates the occupation situation of various flight resources and the position and the state of each airplane of each moment when the airport performs the flight task. The scheduling system computes and issues an action instruction according to the resource state, and each airplane performs each step of operation according to the received instruction so that the accident of airplane collision can be avoided and successful take-off and landing of the airplane can be guaranteed, and the utilization rate of various resources of the airport can be enhanced. The airport flight resource and airplane scheduling algorithm is relatively flexible, and different scheduling algorithms can be designed according to different task types so as to meet the task requirements.

This invention relates to a method used in selecting commercial plastic sealed devices in space including selection and test, reliable computation and anti-radiation test, anti-radiation reinforcement and evaluation based on the above mentioned test result, reliable computation and anti-radiation reinforcement result, which carries out 100% un-destrctive selection tests to eliminate forepart invalid products with potential shortcomings and increases the reliability of batch products.

The invention relates to a rope-driven mechanical finger, comprising a base, a rope driving device, a first finger segment, a second finger segment and a third finger segment. The base, the first finger segment, the second finger segment and the third finger segment are coaxially and serially connected in sequence. Each finger segment includes an upper platform, a lower platform, a center supportmechanism and a plurality of springs, two ends of the center support mechanism are fixed to the center of the upper platform and the center of the lower platform respectively, the center support mechanism can bend and rotate, and the springs are distributed evenly between the upper platform and the lower platform outside the center support mechanism. The rope driving device includes a traction rope, a winding wheel and a driving motor, the driving motor and the winding wheel are fixed to the base, the winding wheel is coaxially connected with an output shaft of the driving motor, the tractionrope is passed through the springs of the first, second and third finger segments, the first end of the traction rope is fixed to the upper platform of the third finger segment, and the second end ofthe traction rope is connected with the winding wheel. The rope-driven mechanical finger has small rotational inertia and high transmission precision and can bend continuously.

The invention discloses an improved predictive guidance method for RLV (reusable launch vehicle) reentry heat flux tracking, and relates to the technical field of flight guidance. According to the method, a longitudinal guidance law and a transverse guidance law in prediction correction guidance are improved, and the method mainly comprises the following steps that when the longitudinal guidance law is designed, firstly, the maximum value of the heat flow rate at the current moment is determined, and then a heat flow rate tracking compensation item is introduced into longitudinal guidance lawdesign to correct the heeling angle amplitude; in the transverse guidance law design process, geographical constraints can be effectively processed by utilizing transverse guidance logic designed by an improved artificial potential field method, and the transverse guidance logic after the reusable vehicle flies over a no-fly zone is determined by a track azimuth angle error corridor. According tothe method, the landing point precision of the aircraft can be guaranteed, and process constraints and geographical constraints in the flight process can be met.

The invention relates to the MAS task distribution field, discloses a contract network distribution method, an obtaining method, an intelligent proxy and an MAS in order to solve the technical problem that the current technology cannot guarantee that the chosen intelligent proxy has the capability to satisfy the task requirement. The method is used for a first intelligent proxy and comprises steps of receiving a task request which is published by a task publishing system, manufacturing a task invitation for bidding which contains task information on the basis of the task request, issuing a task invitation for bidding to a plurality of intelligent proxies, receiving a bidding document transmitted by at least one intelligent proxy of the plurality of the intelligent proxies, and choosing a second intelligent proxy used for finishing the first task from at least one intelligent proxy based on the invitation for bidding. The invention achieves the effect that the chosen second intelligent proxy is guaranteed to satisfy the needs of the first task.

The invention belongs to the related technical field of production scheduling, and discloses a production line scheduling system and method based on multiple intelligent bodies. The production scheduling system comprises a global management module, a controller intelligent body and a sub-controller intelligent body, and the global management module is a manager of the highest level in the production scheduling system and has the highest management authority; the controller intelligent body is the core of the production scheduling system and comprises a resource module, a planning calculation module and a task management module, and the resource module is used for storing resource information of the sub-controller intelligent bodies; the planning calculation module decomposes the task and sends the task to the task management module; the task management module sorts the decomposition tasks according to a priority sequence and then distributes the decomposition tasks to the sub-controller intelligent bodies; and the sub-controller intelligent body is used for executing the task sent by the task management module. According to the invention, the independent operation capability of theintelligent body is ensured, and the working efficiency and management capability of the scheduling system are improved.

The invention relates to a task drive oriented reconfigurable satellite constellation network access decision-making method and system. The method comprises the steps of sensing and receiving a task;judging whether the task is unique or not; directly judging whether an alternative satellite satisfies a function required by the task or not if the task is unique; further judging priorities of the new task and a currently performed task if the alternative satellite satisfies the function; accessing a new network if the priority of the new task is higher, otherwise, discarding the new task; and judging the priorities of a plurality of tasks when the task is not unique, then carrying out function judgment and judging whether to access the network or not. According to the method and the system,when network access decision-making is carried out, features of the task itself, attributes of the alternative satellite itself and the attributes of an environment in which the satellite is locatedare taken into consideration, so the constellation satellite matches the task well; the networking cost is low; additional communication system modification is avoided; the universality is high; and anetworking demand of the existing satellite is also taken into consideration, so the compatibility is high.

The invention provides a task processing system and method. The task processing system comprises a determination unit, a judging unit and a processing unit, wherein the determination unit us suitablefor matching a user behavior message from a business system with one or more event tasks in a pre-established event task list when receiving the user behavior message, so as to determine whether a target event task matched with the user behavior message exists or not; the judging unit is suitable for judging whether the user behavior message accords with an effective task condition corresponding to the target event task or not when the determination unit determines that the target event task matched with the user behavior message exists; and the processing unit is suitable for adding the target event task corresponding to the user behavior message to a task progress list and executing a corresponding operation according to a condition of the task progress list when the judging unit judgesthat the user behavior message accords with the effective task condition corresponding to the target event task. The task processing system provided by the invention is capable of decreasing the development volume and is strong in universality.

The invention discloses a space application-oriented vision measurement system ground simulation evaluation system and a space application-oriented vision measurement system ground simulation evaluation method. The system comprises a camera, a visual marking, an electronic theodolite three-dimensional measurement system, a six-degree-of-freedom digital display adjusting table, an LED lamp array and a solar simulator. The method comprises the following steps that the solar simulator and the LED lamp array simulate space illumination conditions, the six-degree-of-freedom digital display adjusting table fixedly supports the visual marking and drives the visual marking to move at a constant speed, the camera collects a visual marking image and outputs a pose measurement value, the electronic theodolite three-dimensional measurement system obtains a pose truth value between the camera and the visual marking, and the measurement value is compared with the truth value to evaluate the pose measurement precision of the camera. The methods involve extreme illumination environment simulation, extreme motion state estimation and pose measurement precision estimation of the camera. According tothe space application-oriented vision measurement system ground simulation evaluation system and the method thereof, the three-dimensional attitude measurement precision of the space target by the camera in the on-orbit state and the robustness of the camera when the target is in the extreme motion state can be comprehensively simulated and evaluated.

The invention provides a performance requirement-based juxtaposition cloud service system, comprising a computing cluster and a juxtaposition module, wherein the computing cluster includes at least one physical node; and the juxtaposition module constructs at least one virtual machine on the at least one physical node according to a preset parameter, hardware parameter of each physical node and a preset virtual machine construction command. The invention also provides a construction method of the performance requirement-based juxtaposition cloud service system. The virtual machine can be distributed to the plurality of physical nodes in a plurality of manners according to the preset virtual machine construction command so that the performance of the virtual machine meets the task requirement of a user and the user arranges the virtual machine flexibly and efficiently.

The distributed comprehensive reconfigurable electronic system platform architecture disclosed by the invention has the characteristics of high safety, reconfigurability and growth capability. According to the technical scheme, each minimum particle unit is combined with a cross-packet switching device and is organized together through a plurality of point-to-point communication links, so that any interconnection and concurrent transmission among all chips or modules are realized; wired/wireless network communication is carried out between the core node unit and each minimum particle unit based on a TTE Ethernet protocol to form the minimum particle units and the core node unit, information interaction and resource sharing are realized through wired/wireless communication units on respective network switching modules, and an open Switch Fabric comprehensive electronic integrated system is formed; the core node unit serves as a management and control center of the integrated electronic system platform, dynamically loads service reconstruction according to a task instruction of an upper computer, and performs network communication and data distribution based on an open function application service interface.