70 results about "Launch control" patented technology

The invention belongs to the technical field of information, and discloses a subsonic target drone launch control method and system, and the method comprises the steps: obtaining target drone training task data, extracting specific scene parameters from task target diversity, and determining a launch trajectory configuration demand; analyzing the dynamic environment adaptation parameters according to a launching track configuration requirement to obtain a time sequence control precision requirement; a control instruction module is processed in an instruction combination mode, and an initial launching control strategy under the modular design capability is generated; for the initial launch control strategy, analyzing dynamic change in complex environment application, and judging a real-time adjustment strategy demand; if the real-time adjustment strategy requirement exists, flexible configuration of a control system is updated according to the dynamic environment adaptation parameters, and an adjusted launching track is obtained; and generating a target drone control scheme with an accurate training task through the adjusted launching track in combination with scene simulation effect data.

The present application relates to the field of unmanned aerial vehicle and fire fighting technology, especially to a multi-attitude adjusting fire extinguishing bomb launching system and method based on unmanned aerial vehicle, the system comprises: a launching execution mechanism, which contains a fire extinguishing bomb slide, a single-degree-of-freedom rotating guide sleeve capable of being adjusted and locked, an angle driving unit and a state locking unit. The method comprises: constructing a gravity self-adaptive launching execution mechanism; establishing a multi-dimensional collaborative launching decision model based on flight state sensing; and executing a collaborative launching control process. The present application solves or at least alleviates the problem of launching precision decline caused by the deviation of the launching direction of the fire extinguishing bomb from the direction of gravity and the inertial lag during the dynamic flight of the unmanned aerial vehicle, provides a multi-attitude adjusting fire extinguishing bomb launching system and method based on unmanned aerial vehicle, realizes high-precision launching of the fire extinguishing bomb along the preset direction of gravity under various flight attitudes, effectively compensates for the dynamic lag effect, and improves the launching reliability and efficiency.

A mining machine having a hybrid diesel-electric drivetrain with launch control includes a diesel engine, an electric generator in communication with the diesel engine to produce electrical power, at least one electric traction motor, at least one brake resistor, and a power controller including a processor. The processor is configured to initiate launch control by receiving an instruction to initiate launch control, increasing electrical power to the at least one brake resistor, increasing power output of the diesel engine to cause the electric generator to produce the increased electrical power, and, upon receiving a launch command, redirecting the electrical power from the at least one brake resistor to the at least one electric traction motor.

A remote launcher includes a base frame, a cradle, a cradle actuator, and a launch control system. The cradle is pivotably coupled to the base frame and includes one or more skids that are configured to receive and support an unmanned water-based deployable. The cradle actuator is coupled to the base frame and to the cradle. The launch control system includes a communication interface, a processor, and memory having instructions. The instructions direct the launch control system to receive, via the communication interface, one or more wireless launch signals and then, in response thereto, generate at least one cradle control signal to enable the cradle actuator to incline the cradle to a launch angle.

1. The name of the design product: Fireworks launching controller. 2. The use of the design product: for controlling fireworks launching. 3. The design points of the design product: in shape. 4. The picture or photo that best shows the design points: perspective view 1.

This application relates to the field of vehicle technology, and in particular to a method, apparatus, and vehicle for controlling the engine power follow-up in a hybrid electric vehicle. The method includes: in response to the vehicle entering launch control mode, acquiring the current state of charge (SOC) value of the power battery; determining a target follow-up strategy for the engine based on the SOC value, controlling the engine to operate according to the target follow-up strategy, and detecting the release time of the brake pedal; when the release time falls within a preset time window, controlling the engine to switch to target output power operation. This solves the problems of battery overcharging risk and low matching degree between engine power output and driver's launch intention in related technologies, which affect the overall vehicle acceleration performance.

This invention proposes a single or swarm launch control system for unmanned aerial vehicles (UAVs) applicable to different media platforms, enabling rapid pre-launch testing without relying on the UAV's onboard battery. It includes a power module, a satellite communication / positioning module, a network communication module, an intelligent control module, a data exchange module, a gating control module, a channel array, and a connection base. The power module provides DC voltage within the system and power for UAV testing. The satellite communication / positioning module provides location information to UAVs within the device that cannot receive satellite positioning signals. The network communication module establishes a communication network between the launch control system and the UAVs. The intelligent control module processes information within the launch control system, issues commands to other modules, and facilitates information exchange between the launch control system and the UAVs. The data exchange module handles data transmission between the modules within the launch control system.

The invention discloses a vehicle starting control method and related equipment. The method comprises the steps that the current vehicle state, the current clutch pressure, the current engine rotating speed, the current engine operating parameters and the power parameters of a vehicle are obtained; judging according to the current vehicle state, the power parameters of the vehicle and the current clutch pressure value, determining whether the current vehicle is in a sliding parking state or not, and meeting a preset control condition for performing torque control on a transmission; when the preset control condition for torque control over the clutch is met, torque control over a transmission is conducted according to the current clutch pressure, the current engine rotating speed and the current engine operating parameters of the vehicle; and when the preset control condition for torque control over the clutch is not met, the current running state of the vehicle is kept. According to the embodiment of the invention, the driving smoothness can be improved, and the user experience is improved. The method can be widely applied to the field of vehicle control.

The invention belongs to the technical field of unmanned aerial vehicle cluster flight simulation, and discloses an air-based platform dynamic throwing type unmanned aerial vehicle simulation system, which comprises a launching control module, a rocket projectile launching trajectory calculation module and a trajectory generation module, the trajectory and dynamics module is used for simulating the flying, separating and throwing process of the projectile body; the unmanned aerial vehicle behavior module is used for realizing unmanned aerial vehicle physical behavior, animation state and collision detection; the user interaction module is used for providing an interface for interaction between a user and the simulation system; all the modules cooperatively work through data interaction; the system is based on a Pawn-Actor object model, and constructs core entities including a launching ship, a rocket projectile, an unmanned aerial vehicle and a target ship parent class. According to the dynamic throwing type unmanned aerial vehicle simulation system for the air-based platform, a user who needs to throw the unmanned aerial vehicle in the air can be used for testing a cluster cooperation algorithm of the user.

The application relates to an unmanned aerial vehicle aerial fire extinguishing bomb throwing device, belonging to the technical field of forest protection and fire prevention equipment, comprising a mounting seat, a bomb cabin base, a throwing control mechanism and a launching controller, the mounting seat is used for being mounted at the lower part of the unmanned aerial vehicle, the bomb cabin base is installed at the lower part of the mounting seat, a plurality of fire extinguishing bomb cabins are distributed around the bomb nest base, the throwing control mechanism is connected to the lower part of the mounting seat and is distributed at the position opposite to the fire extinguishing bomb cabin at the periphery and the lower part of the bomb cabin base and is used for fixing the fire extinguishing bomb in cooperation with the bomb cabin base, the launching controller is installed on the mounting seat and is used for controlling the opening of the throwing control mechanism. The fire extinguishing bomb throwing device can load more fire extinguishing bombs, and the fire extinguishing bomb throwing device is more convenient to trigger the throwing of the fire extinguishing bomb.

The utility model relates to automatic detection equipment technical field, concretely is a kind of acoustic wave temperature measuring equipment factory automatic detection device, including box, box is provided with monitoring module, control module, display module, data storage module and power module, monitoring module includes pressure sensor group and test hardware, test hardware includes booster cylinder, ASG unit, solenoid valve and ASG launch control unit, solenoid valve is connected with control module, for driving booster cylinder to inflate and ASG launch, pressure sensor group is used to monitor main gas source pressure and booster cylinder pressure, and pressure data is converted into electric signal and sent to control module. The utility model replaces manual operation by automation detection, improves test efficiency and data accuracy, reduces manpower cost, and guarantees acoustic wave temperature measuring equipment factory quality.

The invention discloses an automobile front windshield test device, and relates to the technical field of test devices, the automobile front windshield test device comprises a workbench, a limiting mechanism and an ejection mechanism, the limiting mechanism is arranged on a fixing plate on one side of the workbench, and the ejection mechanism is arranged on a supporting seat on the other side of the workbench. According to the device, the automobile front windshield is fixed through the limiting mechanism, meanwhile, the arranged ejection mechanism adopts the design of multiple ejection holes and is matched with the striking rods in one-to-one correspondence, synchronous striking of multiple points of the front windshield in a single test can be achieved, and compared with a traditional single-station device, the device is particularly suitable for rapid detection of batch front windshields. In the aspect of launching control, through the structural design that the motor drives the shifting plate to trigger the limiting rod, the opportunity that the limiting ball is separated from the limiting groove of the sliding rod can be accurately controlled, it is ensured that the compression amount of the launching spring is consistent during launching every time, then the launching speed and impact force stability of the steel ball are ensured, and the reliability of a test result is improved.

The invention relates to the technical field of computer simulation and automatic control, and discloses a complex system emission control logic simulation and verification method. The method comprises the following steps: fusing a multi-source flight state, environmental perception and task information to construct a multi-dimensional state space representation; outputting a candidate control rule through a logic generation model fused by a graph neural network and an attention mechanism; performing dual verification in combination with formalized semantic verification and safety reachability analysis; and after the verification is passed, smoothly deploying new logic in the isolation sandbox, and performing online fine tuning on the model based on execution feedback. The system comprises a multi-source data fusion module, a logic generation module, a formalized verification module, a logic deployment module and a monitoring update module. According to the method, dynamic evolution and safe closed-loop optimization of launch control logic are realized, and task continuity and control reliability of a complex system under an unexpected working condition are remarkably improved.

The invention discloses a front and rear cabin unlocking structure, an unmanned aerial vehicle throwing cylinder and a use method. The front and rear cabin unlocking structure comprises an outer sliding barrel, an inner sliding barrel, a memory alloy unlocking device and a locking rocker arm, the outer sliding barrel and the inner sliding barrel are in sliding fit to achieve butt joint of the front cabin and the rear cabin, the memory alloy unlocking device releases a throwing cap through memory alloy wire phase change contraction, the locking rocker arm is linked to unlock, and low-impact and high-reliability cabin separation is achieved; the unmanned aerial vehicle launching barrel is integrated with the unlocking structure, the unmanned aerial vehicle launching barrel further comprises a front cabin, a rear cabin, a tail cabin, a navigation flight control system, a launching control system, a parachute system and folding wing external hanging pieces, the front cabin is matched with various unmanned aerial vehicle loads, the folding wings and the navigation flight control system provide unpowered gliding capacity, and the parachute system achieves aerial speed reduction. And the release control system overall plans unlocking and separation actions. The problems that an existing releasing device is large in unlocking impact, poor in adaptability and low in reliability are solved, and the releasing device has the advantages of being high in universality, safe in releasing and outstanding in penetration capacity.

The application relates to a novel unmanned aerial vehicle launching device based on a gear and a rack and a launching control method thereof. The launching device comprises a mounting seat, a steering engine, a driving gear, a rack, a baffle, a camera and a single-chip microcomputer. A central shaft is arranged at the top center of the mounting seat. The steering engine is arranged on the mounting seat below the central shaft. The driving gear is arranged on the output shaft of the steering engine. The rack is arranged between the central shaft and the steering engine and is engaged with the driving gear. A plurality of baffles are arranged on the bases on both sides of the central shaft along the length direction of the rack. The two baffles adjacent to the central shaft are symmetrical about the central shaft. The rack passes through all the baffles. An installation position is formed between two adjacent baffles. The installation position is arranged on the rack. The camera is arranged on the mounting seat directly below the central shaft. The single-chip microcomputer is arranged on the mounting seat. The steering engine and the camera are electrically connected with the single-chip microcomputer. The application has the advantages that at least two different kinds of materials can be hung, and the materials can be launched according to different application scenarios.

Systems, devices, and methods including a launch control box; a multi-pack launcher (MPL) box; and a cable connecting the launch control box and the MPL box, where the cable comprises: an outer jacket, a shielded braid, a first wire, a second wire, a third wire, and a fourth wire, where the first wire and the second wire are shielded by the shielded braid, where the third wire and the fourth wire are outside of the shielded braid, and where the third wire and the fourth wire act as an antenna.

A hybrid electric vehicle (HEV) includes an internal combustion engine, an electric traction motor, a motor / generator, and a transmission. A launch control system includes a controller having one or more processors programmed to (A) operate the HEV in a vehicle launch preparation phase while the HEV is at a standstill, including (i) commanding the internal combustion engine to an engine speed launch target, (ii) performing a spark retardation on the internal combustion engine to limit wheel torque and generate an engine airflow torque reserve, and (iii) commanding zero torque to the electric traction motor; and (B) operate the HEV in a vehicle launch phase, including (i) reducing or removing the spark retardation, and (ii) commanding the electric traction motor to operate at a predetermined torque, to thereby utilize the engine airflow torque reserve in combination with the electric traction motor to provide increased vehicle acceleration.

1. Name of the product in this design: Cable adapter panel (launch control and control system for carrier rockets). 2. Purpose of this design: To standardize the laying of rocket-to-ground cables in the launch vehicle ground control and measurement system, improve the service life of the rocket-to-ground cables, and enhance the efficiency of condition preparation and inspection. 3. The key design feature of this product is its shape. 4. The image or photograph that best illustrates the design's key points: a 3D model.

The utility model relates to vehicle manufacturing technical field, especially a kind of based on ivico chassis's launch control vehicle, including chassis, carriage, integrated launch control equipment, oxygen supplement equipment, oil circuit air compressor, recycling system air compressor, air blower, oiling machine, oil filling equipment, generator and power supply system, the chassis uses ivico second class chassis.This based on ivico chassis's launch control vehicle has remarkable beneficial effect.The highly integrated design integrates multiple oil, gas, electric equipment in carriage, not only save space, improve space utilization, but also realize one-stop service and efficient collaborative work, improve work efficiency and process smoothness.

A vehicle launch control method and device. The method comprises: when a target vehicle is present in front of a vehicle to be launched, acquiring a first longitudinal distance, a first lateral distance and a standstill duration between the target vehicle and the vehicle to be launched, a traffic light, a current longitudinal speed of the target vehicle, a second lateral distance between a non-motor vehicle or a pedestrian and the vehicle to be launched, and a current lateral speed of the non-motor vehicle or the pedestrian; on the basis of the first longitudinal distance, the current longitudinal speed, and the first lateral distance, determining whether the target vehicle meets a launch condition; on the basis of a second longitudinal distance, the second lateral distance, and the current lateral speed, determining whether the vehicle to be launched meets a launch inhibition condition; and when the target vehicle meets the launch condition, the vehicle to be launched does not meet the launch inhibition condition, the standstill duration is greater than a preset standstill duration threshold, and the traffic signal is green, controlling the vehicle to be launched to execute a launch operation. The method can improve the accuracy of reminding for the vehicle to be launched, thereby improving perceived driving experience of users.

The invention discloses an anti-falling safety control method with field angle constraint. The anti-falling safety control method comprises the steps of control time sequence binding before launching, guide module initial value binding before starting control, attitude angle instruction amplitude limiting after starting control, control parameter serialization and rudder resource dynamic allocation. The control time sequence binding means that the starting control time of the aircraft is judged according to the initial launching angle, and when the launching angle is lower than a specific angle, the aircraft is advanced before engine ignition; the initial value binding of the guiding module before starting control refers to optimizing an attitude angle instruction according to a detector constraint, optimizing control parameters before and after thrust establishment, and preventing parameter jumping; the dynamic allocation of rudder resources refers to preferentially allocating the rudder resources of the pitching-off channel, and transition to rolling channel priority is performed after the falling risk is released, so that subsequent overload instruction access is facilitated. According to the method, the emission safety requirement and the detector constraint are comprehensively considered, the control time sequence and the initial control parameters are selected according to the emission state, the emission safety problem is solved, meanwhile, it is guaranteed that the detector normally locks the target, and the overall performance of the system is improved.

The invention provides an aircraft cargo bridge gate launching device. The aircraft cargo bridge gate launching device comprises a launching device projectile body box fixing assembly and a projectile body launching assembly. The launching device projectile body box fixing assembly comprises a launching device mounting platform and a guide rail connecting piece; the launching device mounting platform is fixed on a plurality of rolling rods of a cargo bridge gate in an aircraft cabin through guide rail connecting pieces, and the projectile body launching assembly is fixedly mounted on the launching device mounting platform; the launching device projectile body box is fixed to the launching device installation platform through the front end frame and the rear end frame, and the projectile body is fixed into the launching device projectile body box through the projectile body fixing assembly. The projectile body limiting assembly is arranged in a projectile body box of the launching device and used for limiting the front end of a projectile body. The front airtight element is arranged in an inner cavity of the launching device projectile body box, and the airtight rear check block is arranged at the rear end of the launching device projectile body box. The launching control assembly is in airtight connection with the airtight rear check block corresponding to each projectile body and used for launching the projectile bodies. And the purpose of expanding the multi-purpose use function of the airplane is achieved.

The invention discloses a compatible vehicle power-off control method, and the method comprises the steps: S1, obtaining a short circuit state of a cable network plug, a first state being that two end points on the cable network plug are not in short circuit, and a second state being that the two end points on the cable network plug are in short circuit; s2, automatically selecting a power-off control mode, selecting a first power-off control mode in a first state, and selecting a second power-off control mode in a second state; s3, receiving a power-off control instruction from a geologic test launch control, wherein the power-off control instruction comprises a bus message and a switching value control signal; s4, in the first power-off control mode, when the power-off control instructions are all valid, generating and outputting a high-level power-off control signal to execute power-off; and in the second power-off control mode, when any one of the power-off control instructions is valid, generating and outputting a high-level power-off control signal to execute power-off. According to the embodiment of the invention, the universal design of the power-off control circuit with different requirements is realized.

The application discloses a continuous launching missile launching control device, which comprises a control circuit board, a core circuit board and a timing circuit board electrically connected with the control circuit board; the core circuit board comprises a DSP circuit and an FPGA circuit as a minimum processing system; the control circuit board comprises a communication module, an analog quantity sampling module, a storage module, a switching quantity control module and a power circuit module; the timing circuit board comprises a power-on / off control module for controlling the on / off of a relay according to a switching quantity signal provided by the control circuit board; and the timing control module comprises three-stage control switches which are connected in series, wherein the first stage is a total control switch, the second stage is any one load control switch, and the third stage is a parallel switch group comprising a cover opening switch, a pin pulling switch, a battery activation switch and an ignition switch. The device can solve the problem of the imperfect safety of the launching control mechanism of the traditional continuous launching missile launching control device, and realizes the safe and reliable launching of the continuous launching missile at a specific time and place.

The unmanned aerial vehicle launching system comprises a gun body structure, the gun body structure is made of ABS materials, the front end of the gun body structure is provided with an arm limiting structure and a clamping mechanism, the rear end of the gun body structure is provided with a gun stock, a trigger and a grip are arranged in the middle of the gun body structure, a power source is installed on one side of the gun body structure, and a battery bin is installed in the gun stock; the sighting telescope is integrated above the gun body and is a variable-focus optical sighting telescope; the control system comprises a power supply module, an RTK module and a trigger switch and is used for realizing positioning and launching control of the unmanned aerial vehicle; the control system is integrated in the gun body structure and comprises a power supply module, an RTK positioning module and a control circuit configuration; by integrating the RTK module and the variable-focus sighting telescope, centimeter-level positioning and target guiding are achieved, and the launching precision and locking efficiency of the unmanned aerial vehicle are remarkably improved; the use threshold is reduced; the system supports multi-scene application, has modular expansion capability, and meets large-scale deployment requirements with high reliability and low-cost design.

The utility model discloses a vehicle -mounted unmanned plane launching device relates to unmanned plane launching technical field, including car main part and the chassis of the frame that car main part rear end arrangement, and the upper end of chassis of frame is provided with launcher, the inside of launcher is provided with tool box and launch control box. This vehicle -mounted unmanned plane launching device, will launch the stable combination of frame chassis, and the convenience and mobility of unmanned plane launching have been improved significantly, and the built -in layout of tool box and launch control box makes the operator in the car can complete each preparation work before launching, greatly shortens the deployment time, realizes the flexible adjustment of launcher internal space, makes this launching device can be compatible with multiple models unmanned plane, improves the versatility and economy of equipment, and the cooperation of pressing piece and telescopic rod makes the adjustment process more simple and fast, can be completed without complex tool, greatly improves the convenience of the device use.

The invention discloses a semi-physical simulation system and method for ground separation control of an electromagnetic launch rocket, and the system comprises a launch control module, an electromagnetic propulsion simulation module, a booster simulation module and a communication module, and the electromagnetic propulsion simulation module and the booster simulation module are connected with the launch control module through the communication module. The emission control module adopts real equipment and is used for issuing control instructions to the electromagnetic propulsion simulation module and the booster simulation module through the communication module, and the electromagnetic propulsion simulation module and the booster simulation module generate feedback data according to the control instructions. The emission control module receives feedback data generated by the electromagnetic propulsion simulation module and the booster simulation module through the communication module to form a simulation test process closed loop. By combining the real control module and the simulation module, the vehicle and carrier rocket separation control scene is simulated, the effectiveness of the separation control strategy can be verified, design vulnerabilities can be found as soon as possible, and therefore the research and development period is shortened.

The objective is to achieve efficient control processing. [Solution] The frame-side control CPU executes a launch control process comprising at least the following: a third frame-side control load instruction that sets first information indicating permission to feed game balls in a fourth frame-side control register; a first frame-side control determination instruction that determines whether or not information indicating that balls are being removed is set in the communication system flag; a sixth frame-side control load instruction that sets the value of the fourth frame-side control register in the first frame-side control register when the determination result of the first frame-side control determination instruction is that information indicating that balls are being removed is set in the communication system flag; and a first frame-side control input / output instruction that writes the value of the first frame-side control register to the frame-side control output port.

The invention discloses an aircraft pneumatic catapulting system and a control method, the aircraft pneumatic catapulting system comprises a catapulting machine, a power mechanism, a reset mechanism, a brake mechanism, a launch control system and a catapulting mechanism, the catapulting mechanism comprises a launch platform, an air cylinder, a dragging vehicle, a movable piston and a traction device; the power mechanism comprises a carbon dioxide liquid storage tank, a filling machine, a phase change device, a first electromagnetic valve, an energy storage tank, a second electromagnetic valve and a servo control valve which are sequentially connected through a high-pressure pipeline. Supercritical carbon dioxide in the storage tank is heated to generate phase change expansion, generated high-pressure gas enters the ejection mechanism to drive the ejection mechanism to eject an aircraft, and the aircraft ejection device has the technical capabilities of being wide in energy controllable range, accurate and controllable in ejection force, high in maneuverability, capable of taking off in a short distance and capable of rapidly and continuously ejecting medium and large aircrafts.

The invention particularly relates to a heterogeneous attack unmanned aerial vehicle system. The system comprises an unmanned aerial vehicle subsystem, a task load subsystem, a combat guiding subsystem, a storage and transportation launching subsystem and a command and control subsystem. Different types of seekers are mounted on a universal unmanned aerial vehicle platform to form heterogeneous multi-type attack unmanned aerial vehicles in the system, and heterogeneous unmanned aerial vehicle control is realized by adopting the same ground launching control equipment and method. According to the unmanned aerial vehicle system, multiple targets can be attacked, multiple types of unmanned aerial vehicles are launched on the same platform, and the multiple types of unmanned aerial vehicles are cooperatively used.