153 results about "Onboard computer" patented technology

The invention relates to the technical field of orchard automatic navigation deviation correction, in particular to an automatic navigation deviation correction system for an orchard track power platform. Comprising a chassis, a vehicle control unit, a navigation system vehicle-mounted computer, a laser radar, a navigation control box, a navigation antenna, a steering motor, a differential planetary mechanism, a rotating speed sensor, an edge architecture control box, a driving wheel assembly, a servo valve and a steering pump. The mode that the whole vehicle controller regulates and controls the servo valve to conduct deviation rectification is adopted, the deviation rectification response speed is high, the control precision is high, the high-speed operation working condition of the orchard power platform can be adapted, and the operation efficiency is improved; the swash plate plunger steering pump is adopted to drive the steering motor, the driving power is small, the heat balance stability is good, and the cost is low; the differential steering mechanism is adopted as a deviation rectifying executing mechanism, the transmission efficiency of the power platform is not affected, the steering line type is controllable, steering is stable, the overcorrection phenomenon is effectively avoided, the automatic navigation operation precision is effectively improved, and the automatic navigation deviation rectifying stability of the orchard power platform is improved.

This disclosure extends to systems, apparatus, and methods related to digital tape measure systems including a digital angle-finder, which are able to record and store or transmit to an external device both a length measurement and an angle measurement. These measurements may be able to be recorded individually or together in one “capture” motion, such as pushing a “record” button. Such a system allows a user to easily record a length of material and an angle indicating where and how the material needs to be cut.In some illustrative embodiments, systems in accordance with the present disclosure utilized units of measurement that are displayed by the digital tape measure in a form that can easily be recorded by hand by simple visual reading of the numbers, while simultaneously allowing measurements from the system to be displayed or recorded by the onboard computer.

A locker system comprising: a server having a processor, a memory, and instructions executable by the process; a database to store data relating to the locker system, one or more users of the locker system, and information relating to one or more transfer items; at least one locker unit having at least one locker, a keypad, a door, a door locking mechanism, a camera within an interior of the least one locker and a scale within the at least one locker, and one or more controllers to run the keypad, the door, the door locking mechanism, interior camera, and interior scale and to transmit data to and from the server, an onboard computer, or both; wherein instructions executed by the server, the onboard computer, or both cause a method to be performed, the method comprising: in response to receiving a request from a first user to rent a locker to exchange the transfer item with a second user, assigning the at least one locker to the first user and transmitting a first access code to the first user; in response to detecting input of the first access code, unlocking the door to the at least one locker; in response to detecting a presence of the detected item, obtaining data from the interior camera, scale, or both and comparing the obtained data with data from the database to determine if the detected item is the same as the transfer item; and if the transfer item is determined to be the same item, deactivating the first access code.

The invention relates to a wall-climbing robot system for detecting a coating of a steel pipe truss structure and an application method, and the system comprises a self-adaptive magnetic adsorption mobile platform which can be adaptively and stably adsorbed on steel trusses with different pipe diameters to execute an inspection task; the robot platform is provided with an autonomous positioning navigation system composed of a laser radar, binocular vision and an airborne computer, and the position of the robot is positioned in the steel pipe truss without satellite signals through real-time mapping and a positioning algorithm of tight coupling of laser and vision. The front part of the robot is provided with an electrically foldable surrounding type array camera, so that full-surface coverage type shooting of a steel pipe component is realized, and real-time identification of coating apparent defects is executed in combination with an artificial intelligence disease identification algorithm in an airborne computer; and the lower part of the robot is provided with a telescopic elastic electromagnetic eddy current probe for detecting the thickness of the coating. The method has the advantages that the apparent diseases and the thicknesses of coatings of steel structures such as ceilings of high-speed rail stations and ceilings of large stadiums can be rapidly detected.

The invention provides a method for actively identifying interference and decoy by an inspection unmanned aerial vehicle, which comprises the following steps: acquiring real-time feedback data of each sensor of the unmanned aerial vehicle to obtain first data; constructing an unmanned aerial vehicle virtual anti-decoy training scene, and training an intelligent anti-decoy strategy model in a layered reinforcement learning training mode; quantitatively deploying the intelligent anti-decoy strategy model to an airborne computer of the unmanned aerial vehicle; and taking the preprocessed first data as the input of the intelligent anti-decoy strategy model, performing active identification of interference decoy, and outputting and executing a flight decision in real time. Diversified data samples are provided for anti-decoy training of the unmanned aerial vehicle through a virtual simulation environment; various decoy modes are simulated, and adversarial strategy training is adopted to improve the strategy precision of the model; layered reinforcement learning is adopted, effective decision learning is realized through a hierarchical decision target, and the decision ability of a decision model is improved.

The invention discloses a reusable anti-unmanned aerial vehicle aircraft based on rotary cutting steel blades, and belongs to the technical field of unmanned aerial vehicle countering. The aircraft comprises a seeker cabin, a function cabin, an instrument cabin, a power cabin, a steering engine cabin and a parachute pack cabin. An infrared seeker is arranged in the seeker cabin; the functional cabin comprises a fixed cabin body, a rotating cabin body and a folding and unfolding mechanism, a fixed shaft is arranged at the axis position of the fixed cabin body, N folding steel blades are installed on the rotating cabin body and evenly distributed in the circumferential direction, and the folding and unfolding mechanism drives the folding steel blades to complete unfolding and folding actions. The folding and unfolding mechanism simultaneously drives the rotary cabin to rotate around the axis of the aircraft; a main power supply, an airborne computer, a data chain and an inertial navigation device are arranged in the instrument cabin, and the power cabin provides patrol flight power for the aircraft; a steering engine for controlling the rudder wings to rotate is arranged in the cabin, and a pressurizing device for pressurizing the parachute pack cabin is arranged in the parachute pack cabin. The anti-unmanned aerial vehicle aircraft can be repeatedly used, and the combat time of the aircraft is prolonged to the maximum extent.

The invention discloses an anti-unmanned aerial vehicle aircraft based on folding steel blade rotary cutting, and belongs to the technical field of unmanned aerial vehicle countering. The aircraft comprises a seeker cabin, a function cabin, an instrument cabin, a power cabin, a steering engine cabin and a parachute pack cabin. An infrared seeker is arranged in the seeker cabin; the functional cabin can independently rotate relative to the front cabin section and the rear cabin section under the driving of the motor and release the folding steel blade mounted on the surface of the functional cabin in a folding manner, and the motor drives the functional cabin to rotate at a high speed and drives the folding steel blade to rotate, so that rotary cutting of the target unmanned aerial vehicle is realized; a main power supply, an airborne computer, a data chain and an inertial navigation device are arranged in the instrument cabin, and the power cabin provides patrol flight power for the aircraft; a steering engine for controlling the rudder wings to rotate is arranged in the cabin, and a pressurizing device for pressurizing the parachute pack cabin is arranged in the parachute pack cabin. The anti-unmanned aerial vehicle aircraft is few in component parts, high in reliability, low in cost and high in cost-effectiveness ratio.

The invention relates to the technical field of automobile lamp communication, in particular to an automobile headlamp free optical communication system and method based on stroboscopic modulation. The vehicle-mounted computer receives road condition information and converts the road condition information into an original bit stream, the anti-interference encoder generates an intermediate signal with a check code, the time-frequency interleaver carries out interleaving, the driving circuit modulates the interleaved intermediate signal, and the vehicle lamp receives the modulated signal and sends out an optical signal in a stroboscopic mode; a photoelectric sensor at a receiving end captures an optical signal emitted by a vehicle lamp, a noise reduction filtering module carries out wavelet noise reduction and filtering processing, a judgment decoding module carries out frame positioning, demodulation and verification on the processed optical signal to generate a restoration bit stream, and a vehicle-mounted computer restores the restoration bit stream into road condition information. And the voice broadcast module carries out voice broadcast on the road condition information. According to the invention, stable communication requirements between vehicles and between the vehicle and the sensing equipment in a closed or semi-closed environment in which electromagnetic signals are seriously disturbed can be met.

The invention relates to the technical field of spacecraft computers, and discloses a satellite-borne computer operating system fault tolerance method, which comprises the following steps of: 1, creating a main operating system partition, a standby operating system partition and a boot partition in solid-state storage equipment, installing a universal operating system with the same version in the main operating system partition and the standby operating system partition, the standby operating system partition stores a compressed mirror image file containing complete data of the main operating system partition; and 2, deploying customized boot management software in the boot partition, and configuring a start flag file storage path and a maximum retry time threshold value of the boot management software. According to the operating system self-sensing and self-switching technology provided by the invention, the switching function of the operating system can be completed under the condition that the satellite-borne computer operates in an unattended manner in orbit, and the satellite-borne computer can be ensured to normally start and operate under extreme conditions without directly losing communication.

The density and power consumption of modern integrated circuits, such as Graphic Processing Units (GPUs), Central Processing Units (CPUs), and Network Processing Units (NPUs) is growing rapidly, which necessitates designing advanced cooling systems. Existing solutions for characterizing and validating these cooling system are inadequate. A flexible, scalable Thermal Test Vehicle (TTV) is disclosed which is based on an array of power transistors, measurement / control circuitry, and onboard computer. The TTV is configured for characterizing the performance of electronic cooling solutions under a variety of operating conditions.

A U-Turn signal indicating system includes a controller that connected to a vehicle by a communication plug and is selectively operated by a vehicle component alone or in conjunction with a user input device. The controller is nested within a main body housing and includes a processor, a memory, and power unit. The vehicle communication plug includes a CAN transceiver for communicating with the CAN bus of a motor vehicle. The plug allows the controller to send and receive information with the vehicle's onboard computers that operate the turn signal indicator lights. The controller detects vehicle settings or actions performed by the driver alone or in combination with the actuation of the user input device and instructs the vehicle computer to operate the turn signal lights in a specific pattern that is provided to the vehicle by the controller.

The invention relates to the technical field of spacecraft electronic systems, and discloses a satellite-borne computer multi-stage fault-tolerant starting method which comprises the following steps: step 1, a management FPGA (Field Programmable Gate Array) reads a starting source identification bit of a BIOSBOOT register, and selects a main BIOS (Basic Input / Output System) storage address or a standby BIOS storage address according to an identification bit value; 2, the management FPGA starts a BIOS level watchdog timer corresponding to the BIOS storage address, and the duration of the timer is configured by a BIOSWDT register; and 3, when the BIOS-level watchdog timer is overtime and does not receive the reset signal, the management FPGA modifies the starting source identification bit of the BIOSBOOT register, and a system reset signal is generated. According to the method, the management FPGA is taken as a core, and a double-BIOS redundant architecture and a multi-disk hot standby mechanism are combined, so that the problem of system startup single-point failure caused by BIOS firmware code bit flipping or startup disk physical damage is solved, autonomous fault-tolerant recovery of firmware and a storage medium is realized, and the defect that an existing single-BIOS single-storage-medium architecture cannot self-repair hardware failure is overcome.

The invention discloses a semi-physical simulation system of an underwater vehicle and a control method of the semi-physical simulation system, and relates to the technical field of simulation control. The control system comprises a simulation tester, a depth simulator, a three-axis simulation turntable, a real-time simulator, a rudder load simulator, a visual simulation system, a data acquisition and processing subsystem, a depth sensor, an airborne computer, an inertial unit system, an inertial navigation exciter, a gyroscope and a steering engine. In the integrated navigation system, a non-real-time part comprises a turntable control computer and a triple master console; the real-time part comprises a dynamics kinematics model, a three-axis simulation turntable, a GPS / DVL simulator, an electric thrust driving simulator, a depth simulator and a surge interference model; the underwater self-propelled body control system comprises a strapdown inertial navigation assembly, a control management center, a depth sensor, a rudder feedback potentiometer and a steering engine. The method can be used for semi-physical simulation of an underwater vehicle, and can simulate a navigation environment with variable depth.

A chamber houses a camera, light sources, and an onboard computer. The camera may be an infrared camera. Infrared light source fibers feed into a circumferential adapter ring to illuminate the inside of the eye (retina). The adapter ring contains a central opening through which it fits around the camera lens. The adapter ring contains openings along the circumference for infrared fibers to provide a light source. Another light source is provided for illumination of the external surface of the eye adjacent to the camera.

The present invention relates to the field of aircraft control technology, and more particularly to a method and system for reconfiguring an onboard computer. The method comprises: a controller prioritizing all onboard computers installed on an aircraft; when the highest-priority onboard computer fails, the controller determines a master onboard computer from the remaining onboard computers according to the priority order, and controls the aircraft via the master onboard computer. This method can minimize the impact of onboard computer failures on the aircraft, facilitate the continuity of aircraft operation, and improve the aircraft's on-orbit safety and reliability.

A method for performing direct logging of sensor data in a vehicle network logging system (VNLS) installed on an autonomous vehicle (AV), the VNLS comprising a network switch connected between an onboard sensor of the AV and an onboard computer of the AV, the network switch comprising a logger for logging sensor data to a disk, is described and includes providing a converter node on the network switch; receiving, using the converter node, data generated by the onboard sensor; and converting, using the converter node, the received data to a data record suitable for logging by the logger to the disk.

The hydraulic circuitry of a factory installed automatic automotive transmission is modified to include a check ball and spring to limit balance oil to a predetermined pressure applied to first end of the clutch regulator valve. When the onboard automobile computer ramps up solenoid oil pressure applied to the clutch regulator valve through a gain valve that acts on a first end of the clutch regulator valve, this pressure is opposed by a spring as well as clutch balance oil pressure that is routed and applied to a second opposite end of the clutch regulator valve. The arrangement limits the balance oil pressure applied to the second end of the clutch regulator valve to a predetermined maximum value so the onboard computer regulates the clutch up to that predetermined value. When the pressure / force applied to the second end of the clutch regulator valve exceeds the predetermined maximum value, a check ball disposed at the second end of the clutch regulator valve, held in place by a spring, is displaced and unseated from a seat in a valve bore, resulting in the exhaust or leaking of the balance oil applied to the second end of the clutch regulator valve so that the oil pressure applied to the first end of the clutch regulator valve is no longer opposed by the balance oil applied to the second end of the clutch regulator valve, thereby enabling the clutch regulator valve to quickly move in a direction to complete the shift and to hold added engine power during the shift.

The present application provides a kind of unmanned aerial vehicle impact system and impact control method, the impact system includes mobile computer, data link ground terminal, remote controller and unmanned aerial vehicle flight device;Mobile computer is configured to display unmanned aerial vehicle situation and photoelectric image, while used to send instruction to unmanned aerial vehicle flight device;Remote controller is configured to carry out flight remote control to unmanned aerial vehicle flight device;Onboard computer on unmanned aerial vehicle flight device is configured to run combined navigation algorithm, give the position, attitude and heading information of unmanned aerial vehicle flight device, realize the navigation, guidance and control of unmanned aerial vehicle flight device;Photoelectric module on unmanned aerial vehicle flight device is configured to real-time investigation and identify target;Communication between mobile computer and unmanned aerial vehicle flight device realizes information interaction;The scheme provided by the present application can realize the control of unmanned aerial vehicle flight device, and impact target through remote control, improve impact response speed, reduce impact cost.

The invention discloses a dynamic object detection and tracking method based on laser radar point cloud. The method comprises the following steps: processing a three-dimensional point cloud of a current area obtained by a mobile robot carrying a laser radar in real time through a double downsampling filtering module to obtain a downsampling point cloud, and then clustering to obtain a clustering point cloud of an object in the current area; performing segmentation frame selection processing on the clustering point cloud to obtain a detection area of the dynamic object; and tracking the dynamic object by using a tracking module according to the clustering point cloud and the detection area of the dynamic object. According to the method provided by the invention, the high detection accuracy can be maintained, and meanwhile, the real-time performance is improved to a certain extent; the method can be deployed on an onboard computer of the mobile robot, and is suitable for planning obstacle avoidance of the mobile robot in a complex dynamic environment.

This invention provides a method for actively identifying interference and deception by an inspection drone. The method includes acquiring real-time feedback data from various sensors of the drone to obtain first data; constructing a virtual anti-deception training scenario for the drone and training an intelligent anti-deception strategy model using a hierarchical reinforcement learning training mode; quantitatively deploying the intelligent anti-deception strategy model onto the drone's onboard computer; using the preprocessed first data as input to the intelligent anti-deception strategy model to actively identify interference and deception, and outputting and executing flight decisions in real time. The virtual simulation environment provides diverse data samples for the drone's anti-deception training; it simulates various deception methods and employs adversarial strategy training to improve the model's strategy accuracy; and it uses hierarchical reinforcement learning, through hierarchical decision objectives, to achieve effective decision learning and improve the decision-making ability of the model.

This invention discloses a camera gimbal based on a multi-rotor drone, belonging to the field of drone technology. The drone part includes a center plate main body, a center plate upper plate mounted on top of the center plate main body, landing gear mounted below the center plate main body, and an onboard computer and camera mounted on the center plate upper plate. Sensors are mounted between the center plate main body and the center plate upper plate, and an optical flow meter is mounted below the center plate main body. A 4000mAh 4S large battery is mounted between the landing gear and the center plate main body. The camera of the drone is fixed by a dedicated camera gimbal. A pressure sensor is placed in the center of the camera gimbal's groove. For most monocular and binocular camera models on the market, when placed on the gimbal, the pressure sensor senses the weight and controls the fixing clamps on both sides of the gimbal to automatically clamp the camera. The fixing clamps have a certain angle of change in all directions, allowing the camera to adjust the field of view in all directions (up, down, left, and right).

Method for synchronized sequencing of takeoff of a space launcher comprising one or more on-board computers, a plurality of on-board fluidic equipment including a propulsion system, and a plurality of on-board electrical equipment, this method being implemented in the on-board computer(s) and comprising reversible steps of control / command of the fluidic equipment and reversible steps of control / command of the electrical equipment, said reversible steps of a respectively electrical and fluidic nature being followed respectively by an irreversible step of starting a flight sequence and an irreversible step of starting the propulsion system of the launcher. The reversible steps of control / command and the irreversible steps of start are directly controlled by the on-board computer(s) of the launcher. See Figure 2

A semi-physical simulation test platform of a vertical take-off and landing single aircraft comprises an aircraft semi-physical set system, ground test equipment and a tool set system. The aircraft semi-physical set system comprises a power part serving as a physical part, a physical sensor, a control mechanism, test equipment, an onboard computer, flight control software loaded and operated on the onboard computer, and a power simulator, a control simulator and a sensor simulator loaded and operated on the onboard computer or a ground computer. The ground test equipment comprises a test controller and simulation dynamics software loaded and operated on a ground computer; the tool set system is used for connecting the platform with an external test device and comprises an onboard tool, a ground tool and a tool connecting piece, the onboard tool is used for fixing the aircraft semi-physical set system, the ground tool is used for fixing ground test equipment, and the tool connecting piece is used for movably and detachably connecting the onboard tool and the ground tool. When the platform is used for testing, the cost can be effectively reduced, and the aircraft iteration period is accelerated.

This invention discloses a ground-based experimental system and method for onboard autonomous maneuvering mission planning. It utilizes a ground-based telemetry, tracking, and command (TT&C) simulation module to manage TT&C resource constraints, satellite-ground status, and mission requirements based on the test scenario. An onboard computer equivalent module performs autonomous mission planning based on mission instructions generated by the ground-based TT&C simulation module, generating control commands or mission execution sequences. A spacecraft dynamics simulation module determines the satellite's orbit, attitude, and visibility based on the control commands. A space environment simulation module generates sensor simulation data based on the orbit and attitude. A navigation sensor simulation module initiates or terminates the mission based on control commands and generates measurement data based on the sensor simulation data, sending it to the onboard computer equivalent module. A payload execution simulation module simulates the payload's operation process based on the mission execution sequence. This allows for the simulation and comprehensive verification of the entire mission planning algorithm, from mission injection to execution feedback.

This invention discloses a drone navigation method based on Transformer and hypergraph enhancement algorithms. The method utilizes a gimbal camera to capture drone images and acquires satellite images to construct a drone image-satellite image pairing dataset. The drone image-satellite image pairing dataset is then standardized to obtain a standardized pairing dataset. This standardized pairing dataset is input into a visual positioning neural network based on Transformer and hypergraph enhancement algorithms for training, resulting in a visual positioning neural network model. The visual positioning neural network model is converted into Engine format and deployed to an onboard computer, forming a drone visual navigation module for rapid positioning. This invention's drone visual navigation module combines the advantages of lightweight and miniaturized structure with the performance advantages of fast inference speed and high positioning accuracy. It is adaptable to most drone models and has broad engineering application value.

Techniques are discussed herein for restoring autonomous vehicle operations after one or more onboard computer systems have failed. An autonomous vehicle may comprise a primary compute node (PCN), an active motion compute node (MCN) and a backup MCN. In the event of a fault or failure at the active MCN, the backup MCN can take control of the autonomous vehicle, in an operation referred to herein as a "'backup MCN takeover."Subsequent "active MCN takeback" techniques can be applied to restore active MCN control of the autonomous vehicle, and to relinquish backup MCN control of the autonomous vehicle. If an active MCN takeback is successfully completed, the autonomous vehicle can return to an autonomous mission that was in place prior to the fault or failure at the active MCN.

The invention provides a measurement information time synchronization method and system for optical axis pointing calibration of a laser terminal. The method comprises the steps that S1, a spaceborne computer receives and caches collected measurement data with time codes; step S2, searching time-aligned satellite attitude data from the satellite attitude data to obtain aligned satellite attitude data; s3, performing recursion on the aligned satellite attitude data by using an attitude kinematics principle to obtain satellite attitude data after recursion; s4, searching the two-dimensional rotation angle data with time alignment from the two-dimensional rotation angle data of the laser terminal to obtain aligned two-dimensional rotation angle data; and S5, performing time synchronization on the aligned two-dimensional corner data through a weighted average interpolation method to obtain synchronized laser terminal optical axis pointing calibration data. According to the time information synchronization method provided by the invention, corresponding time synchronization strategies are designed according to different measurement data, and the reliability is good and the precision is high when the method is implemented on a satellite.

This application provides an airborne FC message transmission method based on publish-subscribe, belonging to the field of airborne computer network communication technology. Specifically, it includes establishing publish and subscribe tables based on a client-server model. A terminal, acting as a client, initiates publish and subscribe requests to the server based on network management messages. A switch, acting as a server, processes these requests and responds with network management messages. The method includes: message publishing based on the publish table, message subscription based on the subscribe table, message sending based on the publish table, and message receiving based on the subscribe table. This application's processing scheme reduces maintenance costs, provides a flexible network platform for the system, and offers a feasible basis for runtime message switching planning.

The invention discloses a large-range collaborative navigation method for an extraterrestrial patroller, and relates to the field of computer vision, visual navigation and map splicing. The method comprises the following steps: performing significance analysis based on spectral residual for a right monocular camera, focusing on sight capture of a typical feature region, establishing a visual odometer model of inertial IMU pre-integration, and performing back-end optimization driven by a factor graph; establishing a plurality of extraterrestrial patroller similar region search models based on an improved bag-of-words model, introducing a similarity relative scoring function based on a norm form, setting a relative threshold value of a similarity suppression function, and obtaining an image overlapping region; according to the method, the calculation capability of an airborne computer is considered, a sparse feature point map and patroller pose splicing model is established, complete splicing of overlapped area maps is completed through splicing of small sparse feature point maps, and the splicing precision and the splicing efficiency are improved.

The present invention provides a geomagnetic detection method, device, launch vehicle, electronic device, and storage medium, relating to the field of aerospace technology. The method includes: when a remaining orbit final stage passes over multiple target detection areas on a current target orbit, controlling a geomagnetic detection payload carried by the remaining orbit final stage to obtain geomagnetic measurement data corresponding to the multiple target detection areas in the current target orbit; determining a first orbit change control parameter for controlling the remaining orbit final stage to change its orbit from the current target orbit to the next target orbit based on orbital parameters of the current target orbit and orbital parameters of the next target orbit; causing an onboard computer to control the remaining orbit final stage to change its orbit to the next target orbit based on the first orbit change control parameter; and constructing an Earth magnetic field model based on the geomagnetic measurement data corresponding to each target detection area in the multiple target orbits. The method and device provided by the present invention improve the equipment reuse rate of the launch vehicle's final stage and reduce the cost of geomagnetic detection.