22 results about "Cruise missile" patented technology

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 a hybrid power system for a dual-mode patrolling bomb and a use mode of the hybrid power system, and belongs to the technical field of aviation power. The problem that an existing patrolling bomb power system is difficult to meet the requirements for long-time cruising and instantaneous explosion acceleration at the same time is solved. The system comprises a hydrogen supply mechanism, a hydrogen peroxide supply mechanism, a fuel cell, a motor and a combustion chamber, the hydrogen supply mechanism is connected with an anode of the fuel cell, the fuel cell is connected with the motor, the motor is connected with a propeller, and the hydrogen peroxide supply mechanism is provided with two supply lines. The first supply line is connected with a cathode of the fuel cell through the hydrogen peroxide decomposition unit, the second supply line is connected with the combustion chamber, a first flow regulating valve is arranged on the first supply line, a second flow regulating valve is arranged on the second supply line, a grain is arranged in the combustion chamber, and the grain is spontaneous combustion fuel with a metal framework. The combustion chamber is connected with the exhaust nozzle. The hybrid power device is mainly used for providing hybrid power for the dual-mode patrol ammunition.

The invention discloses a cruise missile distributed path planning method in a dynamic threat environment, which comprises the following steps: S1, generating a threat grid map based on Gaussian diffusion: converting a continuous geographic space of a combat area into a regularized grid matrix, positioning a threat source in the grid matrix in a mathematical mapping manner, and generating a threat grid map; the influence range is diffused through Gaussian radiation of the threat value and the threat radius; s2, low threat path planning based on Euler distance-multi-scale variable convolution: cooperatively calculating distance and threat cost based on a multi-scale convolution kernel, and generating an optimal path; dynamically switching the convolution kernel scale according to a macroscopic threat evaluation result, and synchronously adjusting the resolution of the grid unit; waypoint risk weakening pretreatment is carried out, and connectivity of the starting point and the ending point of the path is ensured. According to the invention, through threat grid map generation and Euler distance-variable convolution collaborative planning, an end-to-end path planning system is constructed, and a feasible method for dynamic threat response and real-time optimization is provided.

The application discloses a kind of multi-cruise missile cooperative penetration off-line three-dimensional trajectory planning methods based on PSO-RPM, it is related to missile flight path planning technical field, comprising: according to the first flight path constraint model of first waypoint constraint, voyage constraint, flight path angle constraint and first threat area constraint, based on particle swarm algorithm, according to particle velocity and position update model, the voyage cost function of first flight path constraint model is solved, the final flight path set of each cruise missile is obtained, and the cooperative speed of each cruise missile is found;According to the second flight path constraint model of cooperative constraint, boundary constraint, control variable and flight path angle constraint, and second threat area constraint, combined with cruise missile dynamics model and second performance index function, the optimal control problem model of three-dimensional trajectory planning is constructed, and the cooperative penetration off-line three-dimensional trajectory planning strategy of cruise missile is obtained based on pseudospectral method solution.The application can efficiently and accurately plan safe trajectory.

This invention discloses an anti-cruise missile interception system, relating to the field of national defense and military technology. The anti-cruise missile interception system includes a blocking net, a towing device, and a high-voltage power supply. The blocking net is attached to the towing device and electrically connected to the high-voltage power supply. The blocking net is woven from chemical fiber or carbon fiber filaments and mounted on a tower or strip-shaped balloon. The high-voltage power supply employs a high-voltage arc radiation device or a high-voltage electromagnetic pulse device. The immense energy released by the high-voltage power supply can disrupt the guidance and control systems of cruise missiles, causing them to deviate from their targets or even triggering an explosion. This invention has significant advantages such as rapid response, high energy, large interception range, automatic interception, ability to counter continuous cruise missile attacks, low cost, and ease of manufacturing. Through dense, carpet-like deployment, it can effectively intercept enemy cruise missiles and loitering munitions, protecting important military bases and targets.

A device for extinguishing at least one fire on open land, in particular in well-wooded surroundings, includes at least one means for introducing at least one extinguishing medium into the source of the fire. The extinguishing medium is a shatterproof detonating device. The means for introducing at least one extinguishing medium may be a gun, a cruise missile, a plane, a drone or a different aircraft

A multi-cruise missile penetration control method based on multi-head attention mechanism belongs to the interdisciplinary field of artificial intelligence and autonomous systems. It constructs a multi-cruise missile adversarial game simulation environment to collect raw high-dimensional situational observation data; designs a multi-head attention autoencoder to model the dynamic correlation of battlefield units using the multi-head attention mechanism, unsupervisedly compressing the high-dimensional heterogeneous observation data into a low-dimensional essential situational representation; constructs a centralized multi-agent flexible actor-commentator reinforcement learning agent based on the dimensionality reduction features, and completes cooperative strategy training by combining a multi-objective composite reward function to output the globally optimal penetration decision; adopts centralized perception and decision-making, and deploys the model to the actual system to form a closed-loop control. This method alleviates the curse of dimensionality, improves situational awareness efficiency, enhances the convergence speed of reinforcement learning training and the robustness of cooperative strategies, adapts to dynamic adversarial battlefield environments, and improves the success rate of multi-cruise missile swarm penetration. It is applicable to scenarios such as military swarm operations and UAV collaborative mission planning.

The application provides a low-subsonic to high-subsonic wide-speed-range deformable aerodynamic layout of a cruise missile, comprising double-axis variable sweep wing mechanisms arranged at the bottom of a fuselage, capable of arbitrarily changing and locking a sweep angle in a range of 0-90 degrees, each double-axis variable sweep wing mechanism comprising an inner wing segment and an outer wing segment, the inner wing segment being pivotally connected with the fuselage at a wing root, and the inner wing segment being adjusted at a front sweep angle in a range of 0-90 degrees; the outer wing segment being pivotally connected with the inner wing segment at a wing tip, and the outer wing segment being adjusted at a rear sweep angle in a range of 0-90 degrees; and the nose being blunt. In the embodiment, the double-axis variable sweep wing mechanism has opposite influence trends of the inner wing segment and the outer wing segment on the center of pressure of the cruise missile during stretching, folding and flying, so as to control the change range of the center of pressure of the cruise missile in a very small interval, and make the wing sweep process have good maneuvering and stability characteristics and flight stability. In addition, the double-axis variable sweep wing mechanism is parallel to the fuselage when being folded, so that the cruise missile is convenient to store and transport, and the storage and deployment capability is improved.

The sub-span and super-span speed domain aerodynamic layout comprises double-shaft variable-sweep-wing mechanisms arranged at the bottom of a fuselage, the sweep angle can be freely changed and locked within the range of 0-90 degrees, each double-shaft variable-sweep-wing mechanism comprises an inner wing section and an outer wing section, the wing root of each inner wing section is in pivot connection with the fuselage, and the wing root of each outer wing section is in pivot connection with the fuselage. The sweep-forward angle of the inner wing section is adjusted within any angle of 0-90 degrees; the wing root of the outer wing section is pivotally connected with the wing tip of the inner wing section, and the sweepback angle of the outer wing section is adjusted at any angle of 0-90 degrees; the machine body is in a flat shuttle shape, and the machine head is in a pointed-end shape. According to the implementation mode, in the stretching, folding and flying processes, the influence trends of the double-shaft variable-swept-wing mechanism on the pressure center focus of the patrolling bomb are opposite, so that the pressure center focus change range of cross-speed domain deformation flight is controlled within an extremely small interval, and the pneumatic control stability is remarkably improved. In addition, when being stored, the double-shaft variable-swept-wing mechanism can be completely folded and parallel to the fuselage and is adaptive to narrow spaces such as a launch canister or a transport case, so that the storage and deployment capabilities are improved.

The utility model discloses a variable wing patrolling bomb structure which comprises a bomb body, a bomb head and a bomb tail, a folding wing is arranged on the bomb body, a front locking mechanism and a rear locking mechanism are arranged on the bomb body, the front locking mechanism is connected with one end of the folding wing, the rear locking mechanism is connected with the other end of the folding wing, and the folding wing is arranged on the bomb tail. A front elastic unfolding mechanism is arranged between the folding wing and the projectile body; the folding wing comprises a first unfolding arm and a second unfolding arm, the first unfolding arm is hinged to the second unfolding arm, a rear elastic unfolding mechanism is arranged between the first unfolding arm and the second unfolding arm, the first unfolding arm is connected with a front locking mechanism, and the second unfolding arm is connected with a rear locking mechanism; the elastic body is provided with a sliding way, a sliding block is arranged on the sliding way in a sliding mode, and the rear locking mechanism is installed on the sliding block. Secondary wing opening can be achieved, the sweepback angle is changed, and the requirement for multi-platform launching from the ground, a fighter plane, an unmanned aerial vehicle and a helicopter is met.

The application discloses a vertical take-off cruise missile with a composite carrier and unmanned aerial vehicle, and relates to the technical field of cruise missiles, which comprises a carrier and at least one unmanned aerial vehicle; the carrier is used for carrying a first combat unit, and a supporting mechanism is arranged on the carrier and can be supported on a fixed surface when the carrier vertically takes off; the unmanned aerial vehicle is detachably connected to the carrier and is used for carrying a second combat unit; the unmanned aerial vehicle can provide thrust when the carrier vertically takes off and attitude is controlled; and the unmanned aerial vehicle can be separated from the carrier to attack a target. The vertical take-off cruise missile with the composite carrier and unmanned aerial vehicle expands the attack range and multi-target attack capability of the cruise missile and improves take-off conditions and cruising capability.

The unmanned aerial vehicle bomb dropping device comprises a hanging plate, an overturning assembly and aerial bomb bin assemblies, the overturning assembly used for overturning the multiple aerial bomb bin assemblies is arranged at the bottom of the hanging plate, one end of each aerial bomb bin assembly is hinged to the bottom of the hanging plate, and the other end of each aerial bomb bin assembly is hinged to the output end of the corresponding overturning assembly. The aerial bomb bin assembly comprises a bin base, a bomb dropping cylinder, an aerial bomb bin body, an elastic locking structure, a launching structure and a rocker structure. The launching structure comprises a cam, a push rod, a roller, a launching spring and an electromagnetic locking structure. The flying bomb has the advantages that through cooperative control of the overturning assembly and the flying bomb bin assembly, the fuze of the flying bomb is always kept in the upward posture in the loading, flying and disassembling processes, the fuze of the flying bomb is sealed in the bomb dropping barrel in the flying process, the bomb body is fixed by the elastic locking structure, external impact and friction are isolated, and the false triggering risk is reduced; and the launching structure has no pre-tightening force when the unmanned aerial vehicle bomb dropping device flies or the bomb is disassembled, so that the risk of accidental release of the pressurized launching structure is eliminated.

The application discloses a high-altitude long-endurance target aircraft combined navigation method and system applicable to satellite denial conditions, relates to the high-altitude target aircraft, general unmanned aerial vehicle and navigation guidance field of cruise missile, and the high-altitude long-endurance target aircraft combined navigation method applicable to satellite denial conditions comprises the following steps: in a take-off preparation stage, a combined navigation unit receives navigation basic information set through a data link; in a take-off stage, the combined navigation unit completes self-alignment based on a current attitude angle of the target aircraft, a current speed of the target aircraft and current position coordinate information of the target aircraft, and then the target aircraft is launched; in a target aircraft flight stage, the combined navigation unit analyzes a PDOP value by using a preset threshold value, determines a current navigation mode, calculates target aircraft navigation state information and transmits the target aircraft navigation state information to a flight control unit, and the flight control unit generates flight control instructions based on the target aircraft navigation state information. The application can realize accurate positioning and navigation of a flight vehicle (such as a target aircraft) in a normal satellite signal environment and a satellite denial environment.

This invention relates to a disc-type folding loitering munition suitable for dense loading of large-caliber rockets, and pertains to the field of unmanned aerial vehicle (UAV) technology. It includes a mother missile, loitering munition bodies, a deceleration parachute, and a partition plate. The mother missile serves as the delivery carrier for the loitering munition bodies, responsible for long-range delivery. The loitering munition bodies are densely loaded in rows within the mission payload compartment of the mother missile, and are isolated and protected by the partition plate. The deceleration parachute is installed on the loitering munition body to decelerate the munitions after release, enabling them to reach normal operating speed. The loitering munition bodies of this invention can be densely loaded onto the mother missile, forming a swarm of loitering munitions after deployment, increasing firepower density and improving combat effectiveness. It is also suitable for loading large-caliber rockets, reducing onboard space occupation and improving usability. Furthermore, the tilt-rotor technology enhances the flight maneuverability of the loitering munitions.

The invention relates to a patrolling bomb launch canister wiring trough bonding device which is of an axial symmetry structure and is composed of a lower machine body, an upper machine body, a pin shaft, a cotter pin and the like. Wherein the lower machine body comprises a front base, a rear base, a lower pull rod, a positioning block and a standard part; the upper machine body comprises an upper base, an upper pull rod, a clamping ring and a pressing plate. The axial degree of freedom, the horizontal degree of freedom, the longitudinal degree of freedom and the rotational degree of freedom of the launching cylinder body are limited by diagonal planes of the front base and the rear base of the lower machine body, diagonal planes of the upper base of the upper machine body and positioning blocks. The axial degree of freedom of the wiring trough is positioned and limited by steps at the front end and the rear end of the cylinder body; the V-shaped faces of the two upper bases on the front side and the rear side of the upper machine body are automatically attached to the two side faces of the wire groove, and after the upper machine body is closed in place and locked, the wire groove is automatically positioned to the circumferential face of the barrel, so that the horizontal degree of freedom and the rotational degree of freedom are limited. According to the invention, accurate positioning before bonding of the wiring trough is realized, consistent pressurization load of the wiring trough can be ensured, and the production efficiency and the process consistency are improved.

The invention provides a position optimization deployment method and system for a ground-to-air missile to resist a cruise missile, and the method comprises the steps: constructing an optimization index according to a plurality of performance indexes of an air defense weapon, and determining a weight coefficient of the optimization index through an analytic hierarchy process according to a decision demand; according to the optimization index and the weight coefficient, constructing a position optimization deployment objective function reflecting the comprehensive efficiency of the ground-to-air missile resisting the cruise missile; and performing optimization searching on the position deployment scheme through a preset intelligent algorithm and the position optimization deployment target function to obtain a position optimization deployment scheme. Therefore, under the condition that an optional alternative position is given, factors such as an enemy attack direction, an important target defense condition, a ground-to-air missile fire coverage area and an interception array surface are comprehensively considered, a ground-to-air missile optimization deployment target function is constructed to search for an optimization deployment scheme of a given ground-to-air missile troop, and the workload and error rate of manual deployment are reduced.

The invention provides a double-shaft variable-sweep upper single-wing layout of a speed-domain-crossing patrolling missile, which comprises a double-shaft variable-sweep wing mechanism arranged on the back of a fuselage and can form an M-shaped integral structure; each double-shaft variable-swept-wing mechanism comprises an inner wing section and an outer wing section, and the wing root of the inner wing section is pivotally connected with the fuselage, so that the sweep-forward angle of the inner wing section is adjusted; the wing root of the outer wing section is pivotally connected with the wing tip of the inner wing section, so that the sweepback angle of the outer wing section is adjusted. In the embodiment, the angles of the inner wing section and the outer wing section can be independently changed, the left side and the right side have asymmetric deformation capacity, and the overall aerodynamic configuration is changed to adapt to different flight speeds from low subsonic velocity to supersonic velocity. The upper single-wing layout is adopted, and space can be released for placement of an air inlet channel and task loads. The high-aspect-ratio wings bend and deform upwards to deviate from the fuselage under the aerodynamic load, and the problem of structural interference of the wings and the fuselage caused by aerobombs is solved. Most airfoils and the whole variable-sweep rotating mechanism are located in the leeward shadow area of the fuselage, so that the stealth performance is improved, and the aerodynamic heating problem of the deformed airfoils during hypersonic flight is relieved.

The utility model belongs to the technical field of small-sized patrolling ammunition launching, and particularly relates to an eight-shot cluster launcher for small-sized patrolling ammunitions, which comprises an upper panel, the bottom of the upper panel is fixedly connected with a bellyband vehicle, the top of the bellyband vehicle is fixedly connected with a connecting seat, and the inner side of the connecting seat is rotatably connected with a rotating rod. The second bevel gear is driven to rotate through the control motor, the rotating rod is driven to rotate through the meshing relation between the second bevel gear and the first bevel gear, and at the moment, the top end of the rotating rod can drive the eight-continuous-shot launching frame installed above the rotating platform cover to conduct 360-degree all-dimensional adjustment; therefore, the direction of the eight-shot launching frame can be adjusted in time through the rotating platform cover rotating by 360 degrees, upwind take-off is guaranteed, an electric push rod pushes a rotating seat, and at the moment, a single-lug connecting ring rotationally connected with the rotating seat drives the eight-shot launching frame to adjust the pitching angle; therefore, the limitation of terrain and airspace on the small-sized patrolling ammunition on the eight-running-shot launching frame is reduced.

The embodiment of the present application relates to an aircraft wing device, comprising a shell, a wing aerodynamic center adjusting assembly, a wing assembly, a linear potentiometer and a cover; the shell comprises a shell body and a slide rail on the inner side wall of the shell body; the wing aerodynamic center adjusting assembly comprises a wing unfolding pushing part and a wing unfolding angle adjusting part; the wing unfolding pushing part and the wing unfolding angle adjusting part are symmetrically arranged at the two ends of the shell body; the wing assembly comprises a wing mounting seat and a wing; the wing mounting seat comprises a wing mounting seat body and a slide groove arranged on the side of the wing mounting seat body; the slide groove is connected with the slide rail; a group of wings are arranged on the top of the wing mounting seat body; the leading edge of the wing is provided with a slide column; the linear potentiometer is arranged on the side of the wing mounting seat body and below the slide groove, and is used for monitoring the axial position of the wing; the cover is arranged on the top of the wing, and the bottom surface of the cover is provided with a slide way, and the slide way is connected with the slide column.

The invention belongs to the field of front strabismus image matching, and particularly relates to a scene matching navigation positioning method for a large-dip-angle front strabismus seeker, which can adapt to a large-dip-angle front strabismus installation mode of a patrol missile visual seeker, realize reuse of the front strabismus seeker by scene matching navigation, and provide stable navigation information in a plain area. Firstly, an image perspective transformation and angle transformation error compensation algorithm is designed to solve the problem of image pixel coordinate system errors caused by a large inclination angle of a seeker, so that the image pixel coordinate system errors are corrected to a coordinate system the same as a reference image. Secondly, an effective area screening algorithm is designed, and the problem that the large-dip-angle front-squint imaging matching success rate is low is solved. Experiments show that the algorithm process designed by the invention can realize the matching success rate of 82% for the large-dip-angle forward squint seeker.