426 results about "Cruise" patented technology

The invention discloses an automatic control method of a four-power-source tiltable aircraft, relates to the technical field of flight control of tiltable aircrafts, is realized based on a PX4 flight control system, and is suitable for a tiltable aircraft provided with four independent tiltable power sources and corresponding tilting execution mechanisms. According to the method, through configuration of a tilting angle control module, a power distribution module and a full-stage flight logic scheduling module, full-stage automatic control of vertical take-off and landing, suspension, horizontal take-off, fixed-point horizontal flight, automatic cruise, one-key return flight, fixed-angle flight, power source fault handling and the like is achieved. Smooth transition of all flight modes is achieved, the stability of the attitude, the height and the position of the tiltable aircraft in different flight stages is maintained, meanwhile, the functions of automatic obstacle avoidance, fault emergency and the like are integrated, flight safety is guaranteed, flight stability and applicability are improved, and the method can be widely applied to various tiltable aircraft operation scenes.

The invention discloses an air-ground collaborative observation unmanned system key target intelligent search method, which comprises the following steps that: an unmanned aerial vehicle carries a positioning module to provide a positioning coordinate, and executes a preset fixed-point cruise task; the unmanned aerial vehicle performs data acquisition on the environment of the cruising area; a height self-adaptive target detection module is adopted to carry out target detection on image data collected by the unmanned aerial vehicle, a rescue target and temporary obstacles generated after a disaster are recognized, coordinate transformation is carried out on the obstacles and target points, and a detection result is mapped to a position under a global coordinate system; transmitting the recognized target point and obstacle coordinates to a ground mechanical dog in real time through a communication module; the ground mechanical dog updates a dynamic cost map according to the received environment information to realize real-time perception of the environment; and the ground mechanical dog performs path planning based on the environment map. According to the method, efficient perception and rapid rescue of the target point can be realized, and the task execution efficiency and the system robustness in the post-disaster complex environment are remarkably improved.

The invention discloses an intelligent driving control method and system for an unmanned ship, and belongs to the field of unmanned driving control. Firstly, the position and speed of the unmanned ship and the positions and speeds of surrounding obstacles are obtained through a sensor and a positioning device, then dynamic path tracking is carried out in combination with global path planning and local path planning, and finally the unmanned ship is driven to sail along an optimized path by controlling the course and an accelerator. Local path planning adopts an improved dynamic window method, and an unmanned ship trajectory prediction evaluation function is modified by introducing a dynamic risk evaluation layer and a rule compliance layer; the dynamic risk evaluation layer is used for designing a collision risk evaluation function to dynamically screen a speed sampling space and rejecting a speed vector conflicting with a predicted trajectory of a moving obstacle; and the rule compliance layer classifies the meeting situation, introduces a rule evaluation function to perform weight correction on the candidate velocity vector, and drives the unmanned ship to generate a course adjustment strategy conforming to the collision avoidance rule. The unmanned ship realizes full-autonomous cruise, high-precision obstacle avoidance and path tracking in a complex marine environment.

The invention belongs to the technical field of numerical simulation and analysis of unmanned aerial vehicles, and relates to a rigid-flexible coupled variable-camber-range deformable wing optimization design method, which comprises the following steps of: obtaining working conditions of an aircraft, determining wing types and basic parameters of wings of the aircraft, and establishing a three-dimensional aerodynamic model of the wings; variable-attack-angle pneumatic simulation is carried out on working conditions of the aircraft in take-off and cruise, optimal camber values and corresponding pneumatic loads of wings under multiple working conditions are determined, and the positions of rotating joints of the deformed wing ribs are adjusted to obtain the deformed wing ribs after primary optimization; dividing the optimization range of the deformed wing rib after primary optimization into a fixed area and an optimizable area, loading an aerodynamic load under the optimal camber value in the optimizable area to perform aerodynamic simulation to obtain a deformed wing rib after secondary optimization, and optimizing the structure; and a deformed wing rib sample is made, performance testing is conducted, and the optimizable area is adjusted till the wing performance meets the preset requirement. The aerodynamic efficiency of the full flight envelope can be improved.

The invention belongs to the field of track planning and intelligent control of a reusable vehicle, and relates to an intelligent track planning method for a cruise section of the reusable vehicle. The method comprises the following steps: constructing a three-degree-of-freedom centroid motion dynamics model of a cruise section vehicle, generating an offline optimal trajectory sample library covering wide working conditions based on a Gaussian pseudo-spectral method, designing a mapping relation between deep neural network learning task parameters and trajectory features, and outputting a high-quality trajectory planning initial value online. The distribution of collocation points is dynamically adjusted in combination with a self-adaptive collocation point method, a nonlinear programming problem is iteratively solved with a high-quality initial value as a starting point, and efficient and accurate optimization of the trajectory is achieved. Simulation results show that the method significantly reduces the sensitivity of online optimization to initial guess, still has fast response ability and high robustness under complex constraint and uncertainty working conditions, effectively improves the autonomous trajectory planning ability of the cruise section of the reusable vehicle, and ensures flight reliability and control precision.

An air drop rack assembly is mounted within the cargo compartment of a cargo aircraft and has a forward part secured to the load deck and an aft part secured to the aircraft cargo ramp. The rack parts have rollers in conveyor assemblies mounted between C-channels which engage skidboards which support smaller aircraft such as gliders or cruise missiles. When the ramp is up two rack parts are tilted with respect to each other. At payload drop, ramp is deployed to bring the rack part conveyor assemblies into alignment. Although the aligned rack parts are spaced apart, when the cargo aircraft is tilted upwardly, the individual payloads on skidboards are discharged out the aircraft aft opening. Cruise missiles or bombs may be supported on a skidboard with a deformable surface, a forward ballast weight, and a spring, such that once launched the skidboard is pushed away from the payload.

The invention provides an aviation permanent magnet synchronous motor control architecture based on master-slave redundancy and model prediction, belongs to the field of aviation electric propulsion control systems, and aims to solve the problems of extreme environment parameter drift, single-fault shutdown, multi-target control conflict, fault diagnosis lag and the like of an existing system. The control architecture comprises a master-slave dual-redundancy control unit, a wide-temperature-range adaptive model prediction control unit, an electromagnetic interference adaptive suppression unit and a multi-dimensional fault tolerance unit. According to the invention, a DSP + FPGA heterogeneous redundant architecture is matched with two-out-of-three voting logic, so that fault non-perception switching is realized; an extended Kalman filter observer is embedded to update motor parameters on line, and take-off / cruise / landing three modes are preset; interference at the frequency band of 100kHz-10MHz is controlled and suppressed through adaptive notch filtering and a sliding mode variable structure; a long short-term memory network is fused to realize accurate diagnosis of early faults, and the system is adaptive to aviation scenes such as electric general aviation aircrafts and unmanned aerial vehicles.

The invention discloses a large-scale cruise ship water chilling unit pipe network cold storage intelligent energy-saving control method based on double-layer deep reinforcement learning, which comprises the following steps: 1, carrying out inherent cold storage engineering modeling on a chilled water pipe network of a water chilling unit to obtain an energy balance relationship between equivalent cold storage capacity and cold release sustainable time of the pipe network and bearable cold capacity; the relationship is used as a physical prior to introduce strategy learning and a security boundary; 2, constructing a double-layer deep reinforcement learning architecture; 3, a safety layer is additionally arranged in the double-layer deep reinforcement learning architecture, the safety layer cuts and projects output feasible regions of a target layer and a sublayer through a hard constraint and barrier mechanism, the water supply temperature, the temperature difference, the start-stop interval, the condensation temperature and the power change rate are ensured, and the maritime affair safety requirement is met; and 4, on the basis of a pipe network inherent cold storage model, a double-layer deep reinforcement learning framework and a safety layer, peak load shifting control of low-load cold charging-high-load cold discharging is achieved, and unit cold energy consumption of the water chilling unit is reduced.

The invention relates to the technical field of aircraft power control, and discloses a hybrid power coordination control method and system for a vertical fixed-wing aircraft, and the method comprises the steps: obtaining the health state data of a battery module, and evaluating the instantaneous maximum discharge power capability of each battery module according to the data, thereby achieving the hybrid power coordination control of the vertical fixed-wing aircraft. And the overall instantaneous maximum discharge power supply capability of the battery pack is obtained through aggregation. Meanwhile, in combination with flight state information and residual mission profile data of the aircraft, the demand of the future key flight stage for the instantaneous peak power is predicted. By comparing the supply capacity of the battery pack with the future demand, whether the risk of instantaneous power shortage exists can be judged prospectively. When a risk is identified, the method can actively adjust a power distribution strategy of the aircraft, including adjusting cruise parameters, optimizing a vertical landing strategy, and adjusting a battery charging strategy.

The invention relates to the technical field of artificial intelligence, and discloses a big data processing-based ship arrival judgment and unmanned aerial vehicle scheduling method, which comprises the following steps of: firstly, acquiring real-time ship data, and constructing a multi-agent ship behavior simulation environment; analyzing ship group data by applying a group evolution learning algorithm, and extracting a ship group behavior mode; based on the extracted behavior mode, identifying main channels and gathering points of ship flowing, and predicting a future ship group distribution trend; constructing an unmanned aerial vehicle cluster collaborative model, designing a task allocation strategy based on regional division and conquering, allocating a proper number of unmanned aerial vehicles to each sub-region, and planning an optimal deployment position and a cruise path; and finally, dynamic adjustment of unmanned aerial vehicle resources is realized, and the unmanned aerial vehicle resources are redistributed in time according to real-time changes of ship group distribution. According to the invention, the ship group distribution trend can be accurately predicted, and efficient scheduling of unmanned aerial vehicle resources is realized.

The invention discloses an engine main bearing resonance parameter determination method and device, equipment and a medium, and relates to the technical field of mechanical state monitoring, and the method comprises the steps: obtaining a current working condition parameter of a target engine, and detecting whether the current working condition parameter meets a state threshold condition in a corresponding cruise state or not; if yes, acquiring corresponding equipment characteristic parameters, acquisition configuration parameters and original vibration data, determining fault characteristic frequency of each element of the main bearing of the target engine, acquiring harmonic amplitude of each order corresponding to the fault characteristic frequency, and constructing a target function; performing global optimization on the target function by using a preset swarm intelligence optimization algorithm according to the target constraint condition to obtain a first resonance parameter; when it is monitored that the impact signal performance index extracted based on the first resonance parameter is lower than a preset threshold value, the first resonance parameter serves as a search starting point, local optimization is conducted on the target function, and a second resonance parameter is output. And the most suitable resonance parameter is automatically selected in the actual operation process.

An electric vertical take-off and landing aircraft comprises a fuselage and a tilt wing. The tilt wing is tiltable relative to the fuselage in a range of tilt wing angles. Control surfaces are arranged at the tilt wings. The aircraft comprises a horizontal stabilizer with an elevator, in particular a stabilator, a vertical stabilizer with a rudder, in particular a fully movable stabilizer, at least one electric engine for powering main propellers arranged at the tilt wing and at least one software control device. The control device is configured to control at least the control surfaces , the main propellers and the tilt wing angle during hover and transition between hover and cruise flight.

A VTOL aircraft (300, 600) includes a lift propeller (312, 612) configured to provide lift during take-off, landing, and hover operations. The lift propellers (312, 612) are configured to stow close to the boom surface (323, 623) when not in use, for example, during a cruise flight, to minimize drag around the surface of the propellers (312, 612). The lift propellers (312, 612) are vertically displaceable relative to the booms (322, 622) when switched to a lift configuration to provide a greater spacing from the booms (322, 622) to improve lift efficiency and reduce unwanted vibrations. The lift propeller (312, 612) may have a fail-safe configuration that allows the propeller (312, 612) to passively move between a lift configuration and a stowed configuration, and to fully rotate even when fully retracted.

The invention discloses an adaptive cruise function test method and device, electronic equipment, a medium and a product. The method comprises the following steps: in a pre-constructed test scene, acquiring surrounding environment information of a test vehicle to obtain environment sensing data; constructing a vehicle surrounding environment model according to the environment perception data; according to the vehicle surrounding environment model and a preset adaptive cruise control strategy, adaptive cruise control is carried out; acquiring operation data generated when adaptive cruise control is carried out in the test scene; and analyzing the operation data according to a preset performance index to obtain a test evaluation result for evaluating the performance of the adaptive cruise control system. The method can solve the problem that a traditional adaptive cruise test method is insufficient in test coverage in a complex dynamic scene.

The invention discloses a ship channel management method and system based on data analysis, and relates to the technical field of data processing.The method includes the steps that a global hexagonal discrete grid structure is constructed, historical operation data are processed through a large arc gridding algorithm to calculate grid density and time potential energy, and accordingly the grid heat level is judged; the method comprises the following steps: acquiring real-time data of a target ship, calculating a comprehensive risk score and a red region intention probability, constructing a multi-dimensional state vector containing a grid level, establishing a hierarchical control strategy, sequentially judging state vector indexes according to priorities, automatically matching emergency takeover, smooth transition, red region strict management or green cruise modes, and generating a corresponding instruction; according to the method, complex space search is converted into efficient integer operation through the discrete grid technology, risk pre-judgment is achieved through the intention probability model, and the problems that in channel management, calculation power consumption is large, pre-warning lags, instruction conflicts exist and the like are effectively solved.

The invention belongs to the technical field of hydraulic engineering monitoring, and discloses a hydraulic engineering inspection system and method, and the method comprises the steps: a positioning monitoring deployment module reasonably distributes the number and positions of positioning monitoring assemblies; the route planning module plans an optimal unmanned aerial vehicle flight route; planning an advancing route, a water entry position and a water surface leaving position of the underwater robot; the cruise monitoring module carries out all-directional inspection on a water conservancy area; the image analysis module identifies abnormal conditions; the infrared data analysis module recognizes abnormal conditions in time; the radar data analysis module identifies abnormal conditions; the comprehensive analysis module comprehensively evaluates the water conservancy condition; the risk prediction module predicts potential problems and risks. According to the invention, the positioning monitoring assembly and the cruise monitoring module are combined to realize omnibearing monitoring of a water conservancy area; omnidirectional three-dimensional inspection is realized, multi-modal data collaborative analysis is realized, abnormal conditions are identified, potential problems and risks are predicted, and possible faults or disaster hidden dangers of water conservancy facilities can be found in advance.

The invention discloses an unmanned aerial vehicle autonomous cruise and obstacle avoidance method and system for a dynamic no-fly zone. Relates to the technical field of unmanned aerial vehicle autonomous navigation and path planning. The method comprises the following steps: issuing and keeping a no-fly zone set static in a task initialization stage; fusing the multi-source sensing data through a layered SLAM mapping module to generate an occupied grid map; performing global path planning by adopting an improved BFS algorithm and a weighted greedy strategy based on a map, and generating a patrol sequence covering reachable points; compressing and smoothing the spliced path to generate a final cruise trajectory; and triggering local trajectory re-planning for sudden obstacles in a non-no-fly zone based on SLAM perception in flight. According to the invention, autonomous cruise and dynamic obstacle avoidance with high coverage rate and low redundancy are realized under the condition of strictly following the constraint of the static no-fly zone.

An aircraft propulsion system includes a hybrid-electric power plant for delivering power to an air mover for propelling an aircraft. The hybrid-electric power plant includes a heat engine operatively connected to a first air mover, and an electric motor operatively connected to a second air mover. The second air mover is positioned on a wing of the aircraft outboard from the heat engine. A method for reducing trailing vortices includes powering a first air mover of an aircraft with a heat engine during a take-off stage, a climb stage, a cruise-stage and / or a descent stage. The method includes powering a second air mover of the aircraft with an electrical motor during the take-off stage and / or the climb stage. The method includes freewheeling the second air mover during the cruise stage and / or the descent stage to generate mechanical energy and reduce wing tip vortices.

The invention relates to the technical field of unmanned aerial vehicle control, in particular to a transition control method of a tailstock type unmanned aerial vehicle, which comprises the following steps of: establishing an inertia, airframe and airflow coordinate system, and constructing a longitudinal dynamic model based on the coordinate system; calculating a velocity trajectory by adopting a polynomial and deriving, solving coefficients by combining initial and conversion completion conditions, and generating velocity, acceleration and jerk trajectories; related variables are calculated according to the kinetic model and the speed trajectory; an expected airspeed and a pitch angle are tracked through an airspeed controller and a pitch angle controller respectively, and an accelerator control quantity and a pitch control quantity are output; and when the conversion time exceeds a specified value, judging whether mode conversion is completed or not according to whether the actual airspeed reaches the cruise airspeed, and if not, continuously tracking parameters. According to the technical scheme, the speed trajectory is smooth and controllable, it is ensured that the unmanned aerial vehicle with any takeoff weight safely completes mode conversion, and the problem that stable and reliable flight mode conversion cannot be achieved for the tailstock type unmanned aerial vehicle with any takeoff weight is solved.

The invention relates to the technical field of aircrafts, in particular to a telescopic wing type aircraft with a self-adaptive duct and a control method, and the telescopic wing type aircraft comprises a rack, a lifting force assembly, a power assembly and an adjusting assembly; the lifting force assembly comprises a telescopic wing mounted at the top end of the rack and an empennage mounted at the tail end of the rack; the power assembly comprises self-adaptive duct sets installed on the two sides of the rack, and the self-adaptive duct sets are located on the two sides of the bottom ends of the telescopic wings and used for preventing airflow from disturbing the telescopic wings. When the unmanned aerial vehicle ascends and descends vertically, power airflow can be sprayed out vertically and downwards almost and cannot be blocked or turned back by wings above, thrust is utilized to the maximum degree to overcome gravity, the thrust-weight ratio and the hovering efficiency are improved, and attitude control is more direct and accurate; in the cruising state, the positions of the self-adaptive duct sets prevent airflow from directly impacting the surfaces of the wings, smooth airflow on the surfaces of the wings is prevented from being damaged, vortexes are prevented from being generated, the power efficiency is improved, and thrust loss caused by airflow impact is avoided.

1. Name of the product in this design: Tour boat. 2. Purpose of this design: This design is intended for use in water-based tourism and sightseeing. 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. 5. The design for which protection is sought includes color. 6. The bottom surface of this product is a part that is not easily seen or cannot be seen during use, so the bottom view is omitted.

The application discloses a kind of based on hybrid power eVTOL unmanned aerial vehicle control method and related device, its method includes: flight control computer is based on flight control instruction obtains the flight phase that eVTOL unmanned aerial vehicle currently is in, the flight phase includes vertical take-off and landing phase, overdrive mode phase, cruise phase and emergency mode phase;The flight control computer indexes to the flight control strategy corresponding to the flight phase that eVTOL unmanned aerial vehicle currently is in;The flight control computer controls the turbine power generation system and / or the power battery pack based on the flight control strategy to N cruise electric drive unit and M vertical take-off electric drive unit on the eVTOL unmanned aerial vehicle Power supply processing.In the embodiment of the application, turbine power generation system and power battery pack are connected in parallel to supply power for eVTOL unmanned aerial vehicle, while combining redundancy flight control system, so as to achieve optimization in voyage expansion and safety performance improvement.

The invention provides a constant-speed cruise quitting method, device and equipment based on operation behaviors, which can monitor whether a driver operates a warning key or not in the constant-speed cruise process of a two-wheeled vehicle, and monitor that the driver operates the warning key under the condition that an instruction of quitting the constant-speed cruise is not received. If yes, the two-wheeled vehicle is controlled to quit the constant speed cruise, so that the operation difficulty of the driver for quitting the constant speed cruise is reduced, the safety risk caused by the fact that the driver does not quit the constant speed cruise due to warning or danger avoiding is prevented, and the safety of the two-wheeled vehicle and the driver is effectively guaranteed; and therefore, the safety and convenience of the two-wheeled vehicle are improved.

This invention discloses an aircraft flight status identification method and system based on ADS-B, comprising: acquiring ADS-B data of the aircraft in real time and caching the ADS-B data in a high-speed cache database; extracting the latest ADS-B data points of the aircraft from the high-speed cache database at set time intervals, and storing multiple consecutively extracted latest ADS-B data points into a fixed-length queue of a preset length to form a temporal ADS-B data sequence; calculating estimated parameters for status determination by combining the aircraft's flight dynamic data with preset geospatial information; and identifying the current flight stage of the aircraft through a state machine model based on the temporal ADS-B data sequence and the estimated parameters, wherein the current flight stage includes one of taxiing, takeoff, climb, cruise, descent, approach, and landing. The method and system of this application improve the accuracy, continuity, and real-time performance of flight status identification.

A aircraft gas turbine engine and operation method, the engine including: a staged combustion system having pilot and main fuel injectors, and operates in a pilot-only range wherein fuel delivers to pilot fuel injectors, and a pilot-and-main operation range wherein fuel is delivered to at least the main fuel injectors. The engine further includes a fuel delivery regulator to pilot and main fuel injectors, which receives fuel from a first and second source containing fuels each with different characteristics. The staged combustion system switches between pilot-only and pilot-and-main range operation when in steady cruise mode, the mode defining a boundary between first and second engine cruise operation range. The fuel delivery regulator delivers fuel to pilot fuel injectors during at least part of the first engine cruise operation with different fuel characteristics from fuel delivered to one or both pilot and main fuel injectors the second engine cruise operation range.

1. Name of the product in this design: Sofa (Cruise Ship). 2. Purpose of this design: For use as a seat or resting place. 3. The key design feature of this product is its shape. 4. The image or photograph that best illustrates the design's key points: the front view. 5. The bottom surface of this product is a part that is not easily seen or cannot be seen during use, so the bottom view is omitted.

The invention discloses a leakage monitoring and positioning device for a self-adaptive cruise pipeline of an underground water delivery system, and belongs to the technical field of pipeline leakage monitoring. The device comprises a C-shaped shell, a cruise trolley, a sensor, an image shooting device, a signal emitter, a marking device and a power and control device. The cruise trolley serves as a carrier to cruise back and forth on a pipeline, the sensor is used for monitoring whether abnormal water exists on the pipeline or not, the image shooting device is used for shooting abnormal areas, and the marking device is used for marking abnormal points and providing striking marks. The self-adaptive cruise trolley is used for cruising and monitoring back and forth on the pipeline, when a sensor monitors an abnormal signal, photographing and positioning are carried out in time, and the signal is transmitted to a ground working room, so that further harm is avoided. The device is convenient to install and high in precision, the leakage position can be accurately positioned, the panoramic picture of the abnormal area is fed back through the PC terminal and the signal transmitter, and the leakage monitoring and early warning problems of the underground water conveying pipeline are solved.

The application discloses a kind of based on real-time positioning and physiological data's cruise ship emergency evacuation guiding system and method, including bracelet terminal, monitoring subsystem, server platform and client;Bracelet terminal is worn in passenger or crew hand, including heart rate sensor, navigation display and prompt unit, wireless communication module and control circuit etc..Heart rate sensor is used to collect the heart rate information of wearer, navigation display and prompt unit are used to display route guide and provide vibration or voice prompt.By constructing dynamic electronic fence based on computer vision, combined with real-time personnel position and channel topological information to carry out evacuation simulation, generate and dynamically adjust the optimal evacuation path, and use physiological data such as heart rate to optimize the evacuation guiding strategy, trigger nearby rescue dispatch for people with abnormal vital signs, so as to improve the efficiency and safety of cruise ship emergency evacuation.

The invention discloses a fixed wing patrol aircraft flight attitude control method, and belongs to the technical field of unmanned aerial vehicles. Aiming at the technical contradiction that high-speed flight maneuverability and weapon shooting stability cannot be compatible, the method achieves breakthrough through the following innovative schemes that a four-wing propeller collaborative framework is designed, and each propeller is provided with a horizontal linear driver to achieve front-back telescopic displacement in the axial direction of a fuselage; in the horizontal flight stage, based on the feedback of a gyro stabilizer, pitching / rolling double-axis attitude accurate control is realized through the cooperative adjustment of propeller position stretching and rotation speed difference; triggering a layered compensation strategy by an ignition event, and synchronously adjusting the horizontal position and the rotating speed of a propeller according to the recoil force direction; and the tail vane intervenes in fine adjustment only when the yaw is out of tolerance. By combining the seamless conversion design of the vertical take-off and landing stage, the three technical problems of height loss without initial-speed deployment, low aerodynamic efficiency of high-speed flight and insufficient shooting precision are solved.

The application discloses a centralized ventilation system for the tail of a cruise ship, comprising a centralized ventilation platform, a ventilation unit and a plurality of exhaust branch pipes; the centralized ventilation platform is arranged on the top of the elevator machine room at the tail of the cruise ship and protrudes upward from the deck of the area where the elevator machine room is located; a plurality of ventilation openings are arranged on the centralized ventilation platform; the ventilation unit is correspondingly arranged on each ventilation opening; the first end of each exhaust branch pipe is connected with the exhaust opening of each room requiring exhaust at the tail of the cruise ship, and the second end of each exhaust branch pipe is connected with the ventilation opening of the centralized ventilation platform; the exhaust branch pipe is used for guiding the gas to be discharged from each room requiring exhaust to the centralized ventilation platform for centralized discharge. The centralized ventilation platform arranged in the application can greatly reduce the number of structural openings of the deck and superstructure, reduces the weakening of the local structural strength of the ship body, and is favorable for guaranteeing the structural safety of the tail of the cruise ship.