14results about How to "Improve combat capability" patented technology

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 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 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 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 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.

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.

The invention discloses a non-singular rapid transfer alignment method for any misalignment angle of a precise air-drop inertial navigation device, which comprises the following steps: after alignment is started, an airborne main inertial navigation device and the precise air-drop inertial navigation device respectively carry out attitude updating under an inertial system, and solve attitude matrixes # imgabs0 # and # imgabs1 # in an inertial navigation sampling period in real time; the method comprises the following steps: establishing a matching model of an angular velocity integral and a specific force integral in an inertial system based on angular velocity and specific force measurement of an airborne main inertial navigation device and a precise air-drop inertial navigation device; a Kalman filtering state equation is established, and Kalman filtering time updating is completed; constructing a measurement equation according to the obtained integral quantity in combination with a state equation; completing Kalman filtering measurement updating; the compensation of the attitude tracking error under the inertial system of the precise air-drop inertial navigation device is completed; and obtaining an attitude matrix at the alignment ending moment of the precise air-drop inertial navigation device. According to the method, transfer alignment can be rapidly completed under simple hovering maneuver of the aerial carrier.

The application discloses a kind of offline consultation method and system based on man-machine cooperation, comprising the following steps: S1, user information input;S2, information real-time synchronization;S3, AI model real-time generates auxiliary speech and differentiates display;S4, consultant refers to the auxiliary speech generated by AI model and user real-time communication;The scheme has the characteristics of reducing professional threshold, improving service lower limit;Liberate the brainpower of consultant, optimize its role;Seamless fusion AI, maintain the sense of immersion of communication.