34results about How to "Improve combat capability" patented technology

The invention belongs to the field of aircraft control, and discloses a composite guidance aircraft guidance control method and system considering flight time falling angle constraint, and the method comprises the steps: inputting target values of flight time and a terminal falling angle according to a specific task requirement; pre-planning a flight path; in the flight process, estimating the current remaining flight time of reaching the target in real time, and performing feedback adjustment on the flight time error; in a flight approaching target stage, calculating a falling angle error in real time according to the attitude and speed of the aircraft, and correcting the flight attitude; through a nonlinear optimal control algorithm, two constraints of flight time and a falling angle are comprehensively balanced; executing mechanisms such as engine thrust, control surface angle and attitude control spray pipes of the aircraft are adjusted in real time according to a composite guidance algorithm instruction; and when the aircraft is about to arrive at the target, final falling angle correction is performed to ensure that the aircraft hits the target at an accurate angle. According to the method, the balance problem between the flight time constraint and the falling angle constraint is effectively solved, and the guidance precision and the task success rate of the aircraft are remarkably improved.

The invention provides a deep reinforcement learning air combat decision-making method based on situation prediction, belongs to the technical field, and solves the technical problem that an unmanned aerial vehicle cannot realize autonomous decision-making and environment self-adaption in a complex air combat environment. According to the technical scheme, modeling is carried out through kinematics and dynamics characteristics of the unmanned aerial vehicle to adapt to the actual flight state; establishing a deep enhanced confrontation environment for unmanned aerial vehicle confrontation training; dynamically evaluating the state of the enemy unmanned aerial vehicle by using an LSTM prediction algorithm, and quickly obtaining the state of the enemy unmanned aerial vehicle at the next moment; and taking reward distribution as input of a decision maker, and inferring enemy unmanned aerial vehicle situation actions in combination with a prediction state and a reward result to realize tracking strike. According to the method, the advantage of machine intelligent calculation and human experience judgment are combined, the intention recognition accuracy of the enemy unmanned aerial vehicle is improved in a complex and uncertain environment, and the decision-making ability and tactical advantages of our unmanned aerial vehicle are enhanced.

The invention discloses an unmanned cluster networking task planning method based on an improved ant colony algorithm, a storage medium and equipment, and the method comprises the steps: firstly determining an unmanned cluster collaborative strike task planning scene, covering task constraints, target cost and expected benefits, and guaranteeing the planning reasonability; establishing a task planning mathematical model by comprehensively considering task execution cost and benefit, task execution quality constraint and technical performance constraint factors; the ant colony algorithm is improved through local and global pheromone updating rules, the limitation of a traditional ant colony algorithm in a complex optimization problem is overcome, the algorithm is effectively prevented from falling into a local optimal solution, the volatilization coefficient is dynamically adjusted, the search efficiency and the convergence speed are improved, and the unmanned cluster collaborative strike task planning problem is efficiently solved.

The invention relates to an unmanned cluster networking equipment resource allocation method and device, and a storage medium. The method comprises the following steps: based on a many-to-many confrontation task scene between an unmanned cluster networking and an enemy defense system, carrying out the resource allocation of the unmanned cluster networking equipment; constructing an unmanned cluster task revenue function, a cost loss function, a confrontation cost function and an enemy defense system damage function; comprehensively considering performance differences and cost benefits of various weapon systems, and constructing an unmanned cluster networking equipment resource allocation model by adjusting weight coefficients and introducing additional items of specific task requirements; and solving the unmanned cluster networking equipment resource allocation model by adopting a differential genetic algorithm to obtain an optimal weapon resource allocation strategy. Compared with the prior art, various complex factors are comprehensively considered, the optimal or nearly optimal equipment resource allocation scheme can be quickly generated, and the overall combat effectiveness and task success rate of the unmanned cluster are remarkably improved.

The invention discloses an unmanned aerial vehicle three-dimensional flight path planning method based on an LBDBO algorithm, and relates to the technical field of unmanned aerial vehicle three-dimensional flight path planning. According to the technical scheme, an unmanned aerial vehicle flight environment is established; establishing a fitness function; an improved LBDBO algorithm is adopted to carry out unmanned aerial vehicle global path planning; and cubic spline interpolation is adopted to obtain a smooth path curve. The method has the beneficial effects that uniformly distributed populations are obtained through Logistic-Tent chaotic mapping initialization, so that the algorithm has better global search capability; variation disturbance is performed on individuals by using a strategy combining Levy flight and Brownian motion, so that a local optimal solution of an algorithm is avoided, and global search and local development capabilities are balanced; and finally, a smooth and stable track is generated through a cubic B-spline curve fitting path. By improving algorithm initialization, variation strategy, path fitting and other aspects, the quality and efficiency of unmanned aerial vehicle flight path planning are effectively improved.

The invention provides a double-adjusting-angle inlet-adjustable guide vane for widening the bypass ratio working range of a fan, which comprises a first main vane, a second main vane, an auxiliary vane, a main shaft A and an auxiliary shaft B. One side of the first main vane is provided with the second main vane and the auxiliary vane, and the auxiliary vane is positioned below the bottom of the second main vane. The main shaft A is arranged at the blade bottom of the first main blade, and the auxiliary shaft B is arranged at the blade bottom of the auxiliary blade and located in the hollow cylinder of the main shaft A. The main shaft A is used for driving the first main blade and the second main blade to rotate. The auxiliary shaft B is used for driving the auxiliary blade to rotate. The first main blade, the second main blade and the auxiliary blade are adjusted through the main shaft A and the auxiliary shaft B, the flow field of an inlet of the fan is adjusted in a partitioned mode, pre-rotation of different degrees is provided for inlet airflow with different blade heights of the fan, the quality of the inlet airflow of the fan is improved, the working efficiency of self-adaptive starting is improved, and the bypass ratio change range of the self-adaptive fan is widened.

The invention provides a solid rocket engine grain embedded with metal wires and application of the solid rocket engine grain. The solid rocket engine grain embedded with the metal wires is a grain body with a cylindrical structure; wherein the grain body contains a burning speed reducing agent, and a metal wire is further embedded between the grain bodies. The grain is divided into layers with different combustion speeds by adding different metal wires and the combustion speed reducing agent, the purposes of setting the combustion speed and thrust of each layer and adjusting the interval time are achieved, and the range, maneuverability, interception capability and combat capability of a missile can be improved by managing the energy of the propellant.

The invention discloses an air combat deep reinforcement learning hierarchical algorithm based on a time scale separation theory, which combines long-period decision and short-period control, and realizes unmanned aerial vehicle autonomous air combat maneuver decision optimization through a two-stage training strategy. Firstly, the state quantity of the unmanned aerial vehicle is separated into a long-period state quantity and a short-period state quantity according to the time scale, the long-period state quantity comprises the position and the relative speed, and the short-period state quantity comprises the roll angle speed, the pitch angle speed, the yaw angle speed and the like. The long-period decision is optimized through a PPO algorithm, and expected values of short-period control, such as an expected roll angle, a pitch angle and a speed, are output; and the short-period control realizes accurate adjustment of the attitude of the unmanned aerial vehicle through a PID controller. The algorithm adopts two-stage training, in the first stage, convergence is accelerated through a single-step reward strategy, and in the second stage, combat performance is optimized through a final reward. The maneuverability and autonomous decision-making ability of the unmanned aerial vehicle in a complex air combat environment are improved, and the method has the characteristics of quick response and efficient learning and is widely applied to autonomous air combat tasks of the unmanned aerial vehicle.

The application discloses an edge air defense node task allocation method and system based on a genetic algorithm and a contract net method, and particularly relates to the following steps: establishing a target threat degree estimation and task allocation model; using an improved hybrid single-parent genetic algorithm to calculate a multi-platform cooperative task allocation problem through integer coding+dynamic double population, tournament selection+reverse order crossover+adaptive mutation genetic operator design, combined with an elite pool update and a mutation strategy triggered by concentration degree of a simulated annealing criterion; and using an improved contract net method to realize dynamic air defense task re-allocation by extending a contract protocol process, introducing a multi-Agent cooperative architecture, designing a consistency auction algorithm and a dynamic bid correction rule, and combining a load-sensitive contract exchange mechanism in view of problems encountered in executing tasks by air defense platforms in emergency situations. The application can rapidly and effectively perform multi-platform cooperative air defense task allocation, dynamically adapt to environmental changes, and improve multi-platform cooperative air defense task combat effectiveness and combat efficiency.

The present invention relates to a video-level dense false target interference suppression method based on repetition frequency clustering. Aiming at the shortcoming that traditional radars cannot distinguish strong threat real targets from a high-confidence dense false target group, a method for accurately suppressing active deceptive interference entering the radar system from the main lobe or side lobe of the radar antenna is proposed. The specific steps include: channel echo over-threshold envelope condensation, repetition frequency histogram construction, multi-order repetition frequency clustering, amplitude stability judgment, and dense false target elimination. The present invention effectively enhances the radar's ability to resist active deceptive interference and improves the radar's target detection probability and combat effectiveness in a complex electromagnetic environment.

The invention relates to the technical field of gun barrel buffers or brake devices allowing recoil or returning to a to-be-launched state, in particular to an anti-recoil device for a rapid fire gun. The anti-recoil device for the fast fire artillery comprises a pressing ring used for being connected with an artillery automatic machine and an elastic buffer used for being connected with a cradle, the elastic buffer comprises a connecting cylinder, a buffer spring installed in the connecting cylinder and a buffer sleeve arranged in the buffer spring in a penetrating mode, the rear end of the buffer spring is fixed relative to the position of the connecting cylinder, and the front end of the buffer spring abuts against the connecting cylinder. A convex shoulder used for pressing the front end of the buffer spring backwards is arranged on the buffer sleeve; the front end of the elastic buffer is connected with a damping buffer, the damping buffer comprises a cylinder body and a damping piston, a piston rod of the damping piston is fixedly connected with the inner joint, and the rear end of the cylinder body is fixedly connected with the outer joint; according to the anti-recoil device for the rapid fire artillery, recoil force can be rapidly weakened, and therefore impact and vibration borne by the anti-recoil device and the whole frame body are reduced.

The utility model provides a trajectory environment collection mechanism, including shell, reading board part, collection module group and detection circuit group, reading board part collection module group along the axial direction of shell from top to bottom sets gradually, reading board part collection module group and detection circuit group are fixedly connected through the terminal strip and screw, when reading board part collection module group and detection circuit group assemble in place, will make the turn and screw cap and install in the shell, and use electronic pouring sealant to pour seal the space between reading board part collection module group and detection circuit group. The utility model discloses a trajectory environment collection mechanism, through the integrated structure design, waterproof performance is excellent, and the anti -interference ability is strong, safe, and the reliability is high.

The present invention discloses an exoskeleton robot neck support integrated device, which relates to the technical field of exoskeleton robot wearable devices, in order to solve the problem that exoskeleton robots at home and abroad lack neck support devices for offsetting the weight of helmets. It includes a helmet, a flexible support arm, a shoulder annular seat, a top rotating assembly for rotating the helmet, a support guide rail assembly for the up and down swinging of the helmet, and a shoulder connecting assembly for the front and rear extension of the helmet; the top rotating assembly is installed on the top of the helmet, the two ends of the support guide rail assembly are respectively connected to the top rotating assembly and one end of the flexible support arm, the other end of the flexible support arm is connected to the shoulder connecting assembly, and the shoulder connecting piece is installed on the shoulder annular seat. The above-mentioned neck support integrated device has a simplified structure, realizes standardized and integrated design, improves the reliability and comfort of the device, and has high practicality.

The application discloses a kind of analysis and prediction methods of high-frequency noise of pod propeller, comprising the following steps: S1, obtain the flow field original data and corresponding high-frequency noise monitoring data under the working state of pod propeller, and pre-process;S2, based on the separated vortex model, construct flow field-noise coupling analysis framework, set the time step and calculation frequency matched with actual working condition, the present application relates to ship propeller noise analysis and prediction technical field.The analysis and prediction method of high-frequency noise of the pod propeller, by constructing flow field-noise coupling analysis framework, the pre-processed flow field data are processed, the vortex structure characteristics of flow field can be captured, and based on the correlation mechanism of vortex structure and noise generation, the contribution of each vortex unit to high-frequency noise is accurately calculated, the vortex unit of dominant noise source is screened, and the dynamic positioning of high-frequency noise source is realized in combination with its space-time position information, which helps to understand the root of noise generation.

The invention discloses a non-welding replacement design method for a high-speed and high-density electric connector based on fuzz buttons. According to the invention, the specification and dimension of the fuzz button contact element are restrained, the PCB design requirement is adjusted, the high-speed interconnection contact stability of the fuzz button connector between parallel plates is improved, and the high-speed interconnection contact stability of the fuzz button connector between the parallel plates is improved. Further, the fuzz button microwave characteristic advantage is utilized, the rate upper limit of electrical signal interconnection between the parallel plates is improved, and the method has non-negligible value and application prospect for further improving the operational capability of aviation equipment.

The application provides a radar, reconnaissance and communication integrated antenna system and a mode switching method thereof.The integrated antenna system integrates radar, communication, reconnaissance and interference functions.The integrated antenna system comprises a main array surface, an auxiliary antenna, an auxiliary channel, a communication modulation and demodulation module, an electronic reconnaissance module, an array surface control module and an information processing platform.The application can realize directional / omnidirectional communication and wideband omnidirectional / directional reconnaissance while realizing the radar function, has the characteristics of compact structure, high integration, low cost and the like, and the wideband and narrowband combined working mode fully utilizes the main array surface resource, effectively reduces the difficulty and cost of preprocessing, and can automatically realize adaptive switching of different modes of the radar, communication and electronic warfare, effectively improves the resource utilization rate and combat effectiveness of the system, and has high engineering application value.

The invention discloses a guidance situation assessment method based on data driving, which comprises the following steps: in an inertial coordinate system, taking an aircraft as a mass point, and establishing a reachable set and an isotimeline model of missile and target parties in a guidance process; according to the reachable set and an isotimeline model, calculating an isotimepoint set for fitting to obtain an isotimeline curve meeting fitting indexes, and taking the isotimeline curve as sample data; establishing a neural network model, training the neural network model through the sample data, and generating a dynamic isotimeline by using the trained neural network model according to the performance parameters and the position information of the two parties under the current situation; and evaluating the guidance situation according to the generated isotimeline. Through the data driving technology, the model can be continuously optimized through continuous learning, and the model trained through supervised learning can more accurately reflect the complex and changeable combat situation, so that the accuracy of situation assessment is improved, and the response speed and combat effectiveness of a command and control system are remarkably improved.

The invention provides a radar error measurement method and system under composite electromagnetic interference, and the method comprises the steps: generating random numbers which obey the normal distribution of specific parameters for all time points in a certain time period through employing a random number generator based on radar characteristic parameters and shipboard aircraft characteristic parameters; and forming a random number sequence to simulate Gaussian white noise and clutter interference signals in the time period according to random numbers of Rayleigh distribution obeying specific scale parameters, so as to obtain instantaneous amplitudes of the Gaussian white noise and clutter interference signals. Then, instantaneous amplitudes of noise amplitude modulation and frequency modulation interference signals are respectively calculated by adopting a specific calculation method, instantaneous power of a composite electromagnetic interference signal is further calculated, and a signal-to-noise ratio of the radar is calculated by adopting the specific calculation method; and respectively inputting the root mean square of the angle measurement error and the root mean square of the distance measurement error into a random number generator, and outputting the angle measurement error and the distance measurement error to realize accurate measurement of the radar error.

This invention discloses a multi-segment, large-angle two-dimensional vector nozzle, its method, and its application, belonging to the field of aero-engines. It includes a circular-to-square section, with a circular interface at the front end connected to the engine outlet, and an angle deflection mechanism arranged along the axial extension direction of the rear square outlet. The angle deflection mechanism includes circumferentially arranged side plates and follower components. Two side plates are symmetrically arranged on both sides of the rear square outlet, and two sets of follower components are coupled to the upper and lower sides of the rear square outlet, respectively, and located between the two side plates. The two side plates and the upper and lower follower components form the jet outlet. The follower components are composed of multiple angle adjustment plates sequentially hinged, allowing relative rotation between adjacent angle adjustment plates. By adjusting the rotation angle of each angle adjustment plate, the deflection angle of the jet outlet is adjusted, achieving a maximum deflection angle of 90°. This invention solves the problem that conventional two-dimensional vector nozzles cannot achieve large-angle vector deflection in the prior art.

The utility model discloses a security shield which comprises a shield body, a sliding frame is arranged on the inner side of the shield body, a sliding shell is arranged at one end of the sliding frame, the sliding shell is in sliding fit with the sliding frame, a buffer spring is arranged between the sliding shell and the sliding frame, a buffer pad is arranged at the other end of the sliding shell, a handheld plate is arranged on the buffer pad, and the handheld plate is connected with the sliding frame. Two sets of sliding frames are arranged on the inner side of the handheld plate and are in sliding fit with the handheld plate, an adjusting knob is arranged at one end of the handheld plate, an adjusting lead screw is arranged at the other end of the handheld plate, threads at the two ends of the adjusting lead screw are oppositely arranged, the sliding frames are matched with the adjusting lead screw, a handheld handle is arranged on each sliding frame, and the handheld plate is arranged on the handheld handle. The equipment can reduce the impact of the shield body on the arm, can adjust the holding structure matched with the arm, and is convenient for security personnel to use.

The invention provides a virtual material interaction method and device, electronic equipment and a storage medium, and the method comprises the steps: displaying a first pickup strategy of a first virtual character and a second pickup strategy of a second virtual character in the same game in a game interface, and selecting one strategy as a target pickup strategy, and then controlling the first virtual character to pick up the virtual material according to the target pick-up strategy. The interaction efficiency can be improved.

The utility model belongs to unmanned plane technical field relates to a combination structure for strapdown unmanned plane and launching device, and unmanned plane is more and more widely used in military application, unmanned, accurate attack becomes the mainstream trend of modern war, need a new type of load pylon to satisfy these demands, ensure that unmanned plane can efficiently, safely complete its mission, the utility model not only enhanced the security of traditional pylon, also greatly promoted the operation efficiency, in addition, the optimized structure design makes the whole system more compact and light, is suitable for the application demand of modern unmanned plane platform, can realize that unmanned plane carries multiple different types of weapons and ammunition, and copes with different types of combat.

The utility model discloses a multifunctional protective device for combat personnel, which comprises a first protective cabin and a second protective cabin, one end of the first protection cabin is communicated with the tunnel type defense fortification; a first protective cover is arranged at one end, communicated with the tunnel type defense fortification, of the first protective cabin; wherein the first protective cover is connected with the first protective cabin through a spring hinge; or the first protective cabin is vertically arranged, a first protective cover is arranged at the top end of the first protective cabin, and the first protective cabin and the first protective cover are connected through a spring hinge; the first protective cabin is vertically buried under the earth surface, and the first protective cover is flush with the earth surface. Combat personnel can use the multifunctional protection device to realize hiding and protection; the multifunctional protection device is used for observing the surrounding environment and carrying out combat; the multifunctional protection device is simple in structure, easy to deploy and flexible, and effectively improves the protection ability and combat ability of personnel.

The present application relates to the field of aircraft flight mechanics and flight control, and particularly relates to a distributed overdrive tilting wing aircraft control strategy analysis method, comprising the following steps: step one: determining a rudder distribution scheme; the rudder distribution scheme is determined based on a minimum control energy fusion method; the control of multiple aerodynamic rudders is always linked without considering the flight conditions of the aircraft; in order to fully exert the efficiency of the linkage of multiple aerodynamic rudders, the weighted minimum control energy principle is used to distribute the control input, so as to use the rudders with high authority and high efficiency as much as possible under the same control input, and as little as possible to use the rudders with low authority and low efficiency, and finally make all the rudder angles as small as possible; step two: determining a flap aileron bias scheme; step three: calculating the lift propeller speed.

A vehicle long mirror reset lifting device comprises a lifting platform combination, a fixed platform combination and a driving device, the driving device comprises a left electric cylinder and a right electric cylinder, the left electric cylinder and the right electric cylinder are connected through a coupler, a lifting motor is arranged at the front end of the left electric cylinder, and the fixed platform combination comprises a locking cylinder installed above the left electric cylinder and the right electric cylinder. The upper end of the inner cylinder wall of the locking cylinder is fixedly connected with a seat ring, the lower end face of the seat ring is fixedly connected with a locking speed reducer through a gear ring, the upper end face of the seat ring is provided with a supporting cylinder installation bottom plate in the lifting platform combination, and the upper end face of the supporting cylinder installation bottom plate is fixedly connected with a supporting cylinder. A supporting plate is arranged on the circumference of the outer wall of the bottom of the supporting barrel, piston rods of the left electric cylinder and the right electric cylinder penetrate through the supporting plate and then are fixedly connected with an upper end flange of the supporting barrel, and the top of the supporting barrel is provided with a vehicle length mirror.

The invention relates to the technical field of liftable front steering knuckle systems, in particular to an amphibious vehicle liftable front suspension which comprises a main steering knuckle beam, an adjusting mechanism is movably connected to the interior of the main steering knuckle beam, lifting damping mechanisms are movably connected to the two sides of the top of the main steering knuckle beam, and a steering mechanism is arranged on one side of the bottom end of the main steering knuckle beam. A control mechanism is arranged on one side of the main steering knuckle beam, when the amphibious vehicle runs on the land, the lifting front suspension plays a role of a common steering knuckle, and impact borne by the vehicle in the running process and vibration of a vehicle body are buffered; when the amphibious vehicle runs in water, the lifting front suspension lifts the steering knuckle mechanism and the wheel system through the hydraulic oil cylinder, the purposes of reducing resistance and increasing running speed are achieved by reducing eddy current loss caused by the running mechanism stretching into the water, and the loss of the steering knuckle system can be effectively reduced.

The invention provides an effective electromagnetic suppression distance prediction method and device, equipment and a storage medium, and particularly relates to the technical field of electromagnetic spectrum management and control. According to the method, radio wave propagation path loss, the maximum receiving power of a target radio station, a frequency suppression factor and interference equivalent radiation power are calculated by obtaining spectrum characteristic parameters of electromagnetic management and control equipment and a suppressed target radio station, and further, the effective electromagnetic suppression power of the target radio station is calculated by combining a radio frequency protection rate, a harmful interference coefficient and the like. And calculating and outputting the effective suppression distance of the electromagnetic control equipment to the target radio station according to the parameters. According to the invention, key spectrum characteristic parameters of an electromagnetic space in a frequency domain, a space domain, an energy domain, a signal domain and the like are introduced, so that the problem that the electromagnetic suppression capability of electromagnetic control equipment is difficult to comprehensively and visually display in the prior art is solved, and the control capability and combat effectiveness of an electromagnetic environment are improved.

The invention discloses a comprehensive weapon system control method which comprises the steps that external information is obtained and sent through a sensing module, and the external information is converted into a unified format and protocol through a control information converter and an image information converter to be transmitted and displayed on a display control module; an operator terminates the operation of the information or sends out control information through the command control module, and the control information converts a unified protocol into a protocol for direct communication of each execution module through the control information converter and transmits the protocol to each execution module; each execution module responds to the outside according to the control information, converts the responded outside information and own running state information through the control information converter and the image information converter, and transmits the converted information to a display control module in the control module; an operator decides to end operation or send out control information according to information on the display control module, and closed loop control over the whole weapon system is achieved.

The present invention discloses a separable flying wing layout unmanned aerial vehicle, including a flying wing layout unmanned main aerial vehicle located in the middle, flying wing layout unmanned sub-aviation vehicles seamlessly and symmetrically arranged on the left and right sides along the central axis of the flying wing layout unmanned main aerial vehicle, a main engine connecting rod fixedly connected to the lower wing surface of the flying wing layout unmanned main aerial vehicle at one end, and a sub-machine separation mechanism fixedly connected to the lower wing surface of the flying wing layout unmanned sub-aviation vehicle and detachably connected to the other end of the main engine connecting rod. During the flight, the sub-machine separation mechanism is separated from the main engine connecting rod to realize the separation of the flying wing layout unmanned main aerial vehicle and the flying wing layout unmanned sub-aviation vehicle. Based on the original load and mission, the present invention can split an aircraft into multiple small aircraft on the way to perform a mission, and apply it to military and civilian fields through multi-UAV cluster control technology.

The application provides a water, land and air integrated maritime combat scene situation awareness method and system based on a large model, relates to the field of military combat, and comprises the following steps: acquiring water, land and air multi-source combat data and performing space-time alignment processing; performing parallel feature extraction on the data aligned by each mode, and performing dimension reduction on the extracted features through an adaptive bottleneck layer of the large model; based on the feature vectors of each mode after dimension reduction, constructing a multi-level attention bottleneck unit in the large model, and respectively distributing each mode feature vector to a corresponding level for attention weight calculation; realizing dynamic fusion of different mode feature vectors through feature splicing and an attention mechanism, inputting multi-modal fusion information into a classifier of the large model for battlefield situation assessment, and generating a dynamic strike decision scheme according to the assessment result. The application is used to solve the defects in the prior art that multi-source heterogeneous data processing exists inter-modal conflicts, and it is difficult to realize efficient situation awareness and accurate strike decision.