10 results about "Launch control" patented technology

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.

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 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.

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 application discloses a kind of electric control cannon shooting unmanned aerial vehicle systems based on high-pressure cold gas ejection, cannon tube bottom is equipped with cannon tube rear end cover, cannon tube rear end cover is connected with cannon tube by bolt;Firing control module is located in the bottom end inside cannon tube, firing control module lower end is connected to gas storage module;Firing control module upper end is connected with the lower end of propellant gas cylinder module;Propellant gas cylinder module upper end is connected with the lower end of separation module by bolt;Unmanned aerial vehicle module is placed in the cup-shaped space of two L-shaped blocks on the upper end of separation device, only when 2 L-shaped blocks separate, unmanned aerial vehicle can be released.The application makes unmanned aerial vehicle obtain higher power by air secondary separation operation, and the effective working range of rotor unmanned aerial vehicle is larger;Secondary separation device and nose cooperate design significantly improve the overload capacity of unmanned aerial vehicle;Only use built-in trace gunpowder straight thread sleeve and spring connection, greatly reduce the amount of gunpowder and cost;Modular design makes production and manufacture simple, and batch production can meet the teaching needs.

A control system for road building machines, particularly pavers, that automatically transitions the machine between operational states using closed-loop feedback control to achieve consistent paving joints. The system comprises a speed input mechanism for setting target speeds, a launch control input for initiating transitions, a controller executing closed-loop feedback control algorithms, and sensors monitoring machine speed, position, velocity, acceleration, and electrical current. The controller automatically generates controlled acceleration profiles using real-time sensor feedback to transition the machine from a first operational state to a second operational state, where each state may be either stationary or moving at a specified speed. This enables consistent transitions when starting from rest, accelerating to higher speeds, decelerating to lower speeds, or stopping, thereby eliminating variability in joint formation caused by manual operation. Optional directional control provides emergency stop functionality. The system may be retrofitted to existing equipment or integrated into new machines, and can be implemented through software updates to existing control systems.

The utility model discloses a kind of long-distance multi-path controllable rocket booster launch control equipment, it is related to rocket power control technical field, including operation end, launch control end and the communication module of connecting both, operation end surface is equipped with power switch, unlocking button, ignition button, test button, mode selection knob and display unit.The utility model provides launch control distance long, its launch control distance can reach 800 meters, this characteristic effectively eliminates the security risk that relevant operating personnel is brought because launch control distance is too short, provides more safe working environment for operating personnel;Multi-path rocket booster launch control can be realized, with the ability of multi-path rocket booster launch control, can fully meet the demand of multi-machine cooperative control, and the strict requirement of high reliability and high safety under complex working conditions, guarantee the smooth progress of rocket launch mission.

1. Name of the product in this design: Dynamic graphical user interface for vehicle launch control of electronic equipment. 2. Intended use of this design: for use in an electronic device. 3. The key design feature of this product is its graphical user interface. 4. The image or photograph that best illustrates the design's key features: the front view. 5. Purpose of the graphical user interface: a dynamic interface used for vehicle launch control. 6. Human-computer interaction method of graphical user interface: When the vehicle is in the launch start state, the interface changes dynamically from the main view to the interface change state Figure 21. 7. Other situations requiring explanation: Each single gray block in each view represents a content screen, and the "X" in the figure represents replaceable text or numbers.

This application belongs to the field of unmanned aerial vehicle (UAV) control technology, and particularly relates to a heterogeneous UAV deployment control method and system based on separation disturbance feedforward. The method includes: firstly, acquiring the initial attitude angle, initial angular velocity, initial separation velocity, and real-time three-axis acceleration and angular velocity of the rotor-wing UAV at the moment of separation; simultaneously, solving for the feedforward compensation quantity by constructing a separation disturbance observer; secondly, predicting the evolution of the unpowered descent trajectory of the rotor-wing UAV using numerical integration; then, constructing an optimization function to solve for the optimal acquisition time and determining the acquisition window; finally, calculating the collective pitch control quantity and the cyclic pitch control quantity and converting them into rotational speed control commands. This application solves the contradiction between strong disturbance and fast take-off control when a fixed-wing UAV deploys a rotor-wing UAV, and achieves a smooth transition from the descent state to the hovering state in low-altitude, high-speed deployment scenarios.

The application discloses a general design method for host computer software of an upper and lower computer structure aircraft launch control system and belongs to the technical field of aerospace launch control. The method comprises the following steps: first, generating a standardized interactive data description file, defining the name, address and other attributes of each launch control data item; second, designing access functions including single write, single read and batch registration; third, constructing a configurable man-machine interface, including a tree list area, a control icon selection area and a user-defined canvas area, supporting drag-and-drop to associate launch control data items with controls; fourth, presetting standardized running control functions; and finally, connecting with the lower computer by calling the control functions to realize the control of the lower computer. The application solves the problems of repeated development of host computer software due to differences between different types of aircraft, long development cycle and the like, realizes high reuse, rapid configuration and flexible expansion of the software, significantly improves the development efficiency and reduces the development cost.