64 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 present application provides a magnetoresistive mover and a magnetoresistive cruise missile launcher. The magnetoresistive cruise missile launcher includes a barrel, a magnetoresistive mover, multiple coils, and multiple sensors. Through the arrangement of multiple soft magnets, during a launch process, the sensor detects the soft magnet multiple times, and the corresponding coil generates a constant magnetic field multiple times, applying electromagnetic attraction toward the launch end to the magnetoresistive mover multiple times, thereby shortening the launch device length and saving costs. By designing the length and distribution distance of each component, the sum of the length of the coil and the spacing length of adjacent coils is equal to the spacing length of adjacent soft magnets, which is equal to the sum of the lengths of all soft magnets. In this way, during the launch process, the magnetoresistive mover is continuously subjected to the electromagnetic attraction toward the launch end, so that the magnetoresistive mover continuously accelerates and pushes the cruise missile, avoiding multiple collisions and impacts on the cruise missile and reducing damage to the cruise missile.

The present application provides a magnetic induction type mover and a magnetic induction type loitering munition launching device. The magnetic induction type loitering munition launching device includes a barrel, a magnetic induction type mover, a plurality of coils and a plurality of sensors. Through the arrangement of a plurality of magnetic induction bodies, during a single launch process, the sensors detect the magnetic induction bodies multiple times, the corresponding coils generate magnetic fields multiple times, and an electromagnetic repulsive force in the direction of the launch end is applied to the magnetic induction type mover multiple times, thereby reducing the length of the launching device and saving costs. Through the design of the lengths and distribution distances of each component, the sum of the length of the coil and the distance between adjacent coils is equal to the distance between adjacent magnetic induction bodies, so that during the launch process, the magnetic induction type mover can continuously receive an electromagnetic repulsive force in the direction of the launch end, continuously accelerating the magnetic induction type mover to push the loitering munition, avoiding multiple impacts on the loitering munition, and reducing the damage caused to the loitering munition.

The utility model relates to a protective isolation device for detecting the electrical performance of a patrol bomb launch canister, which is used for realizing all-directional isolation protection when the electrical performance of the launch canister is detected. The device is composed of a box body, a movable baffle, a saddle, a hinge, a box cover, a lock plate, a lock pin and a supporting rod. A baffle, a front support plate and a rear support plate are sequentially welded in the box body, and a front saddle and a rear saddle are fixed on the box body through bolt assemblies; the box cover is like a door leaf and is connected with the box body through a hinge, and the box body and the box cover are locked through a lock plate and a lock pin. According to the device, the launching cylinder is sealed in a limited space, axial flying of the launching cylinder after mistaken ignition is limited, flying of high-temperature fragments of combustion explosion or structural disintegration is also limited, meanwhile, the box cover pressure relief hole plays a pressure relief role, pressure relief reaction force acts on a working table where the device is located downwards, transverse movement is avoided, and the device is safe and reliable. Therefore, all-around isolation and protection functions are achieved for surrounding detection personnel, equipment and facilities.

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 utility model relates to a vacuum test device for leakproofness detection of a patrol bomb launch canister. The leakproofness of the launch canister is judged by putting the launch canister into a vacuum test cavity, vacuumizing and observing the pressure drop of a vacuum gauge. The device is formed by sequentially connecting an exhaust valve, a vacuum test cavity (including a vacuum meter), a control valve, a pneumatic pipeline, a pneumatic flow regulating valve, a switching valve, a vacuum buffer tank (including a stop valve) and a vacuum pump according to the air exhaust direction. During vacuumizing, the vacuum pump is started to vacuumize the vacuum buffer tank, after a certain vacuum degree is achieved, the buffer tank serves as a vacuum generator to vacuumize the vacuum test cavity, the air exhaust rate is adjusted and set through the pneumatic flow adjusting valve, and opening and closing control over an air channel is achieved through the control valve. The vacuum buffer tank serves as a vacuum generator, frequent starting and stopping of a vacuum pump are avoided, and the service life of equipment is prolonged; the test requirements of multiple products can be met through one-time evacuation, and the test efficiency is improved; the air exhaust rate is stable and adjustable, and the consistency of product test states is ensured.

The present application provides an open reluctance cruise missile launcher, comprising a mounting frame, an electromagnet group disposed in the mounting frame, and a reluctance mover disposed in the electromagnet group. The launcher adopts the principle of electromagnetic induction for launch, and the cruise missile is pushed by the reluctance mover, which is disposed in the electromagnet group, which is disposed in the mounting frame. The mounting frame is an open structure, and is provided with multiple external air channels. The electromagnet group is an open structure, and is composed of multiple electromagnets and a number of guide rods. Internal air channels are formed between adjacent electromagnets. The air inside and outside the launcher can be quickly circulated through the multiple internal air channels and the multiple external air channels, which can effectively reduce the air resistance encountered by the cruise missile during launch, and can obtain the required muzzle velocity in a very short time. In addition, the noise during launch is greatly reduced, and the concealment is improved.

The invention relates to the technical field of intelligent ammunition, and discloses a coaxial multi-rotor patrol ammunition which comprises an integrated control part, an ammunition body part and an integrated power part, a plurality of first propeller blades and second propeller blades are connected to the integrated power part, and a seeker is connected to the outer wall of the integrated control part; the adjustable shielding mechanism is connected to the other end of the projectile body part in a sliding manner; the elastic energy releasing mechanism is connected between the adjustable shielding mechanism and the projectile body part; the shape of the adjustable shielding and preventing mechanism can be adjusted according to the flight attitude, and when entering an attack state, the adjustable shielding and preventing mechanism is in an unfolded state, so that a conical protective cover is formed, the whole projectile body part and the flight structure can be effectively covered for protection, wind resistance is reduced, and the service life of the projectile body part is prolonged. And meanwhile, the elastic energy release mechanism can be used for partially converting the resistance generated by the attack on the conical shield into reverse jet power, so that the kinetic energy loss during the attack of the flying projectile is effectively reduced.

The invention discloses a method for selecting a weak environment information active sensitive device of a patrolling ammunition fuze, which comprises the following steps of: selecting a function, calculating scores, and selecting an active sensitive device with the highest score to detect weak environment information; the selection principle comprises the measurement precision, the installation performance, the frequency response range, the detection sensitivity and the linearity of the active sensitive device and the measurement precision under the change of natural environmental factors. According to the method, the patrolling ammunition fuze can select the active sensitive device with the optimal performance to sensitize the environment characteristics according to the weak environment information available in the outer trajectory flight, so that fuze researchers do not need to select the sensitive device depending on experience, trial and error are avoided, the fuze research and development period is shortened, and the process cost is reduced; and the fuze can be reliably sensitive to weak environment information.

The present invention discloses a pneumatic dimensional mechanism and a pop-up total pressure sensor. The mechanism comprises a dimensional baffle (21), an elastic torsion bar (22) and a wedge pin (23); the dimensional baffle (21) comprises a dimensional base plate (213), one end of the dimensional base plate (213) is provided with a lap ear piece (211), and the other end is provided with a hinge (212); the hinge (212) is connected to a total pressure probe hinge seat (121) at the root of a total pressure probe (12) of a pop-up total pressure sensor (1) via the elastic torsion bar (22); the rotation between the hinge (212), the elastic torsion bar (22) and the total pressure probe hinge seat (121) is limited by the wedge pin (23). The present invention can reduce the negative impact of the pop-up total pressure sensor, reduce the aerodynamic drag during the flight of a cruise missile, and improve stability.

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.

The invention discloses a four-rotor missile wing patrolling bomb which comprises a patrolling bomb head, a patrolling bomb middle and a patrolling bomb tail which are arranged from front to back, a reset spring is arranged in the patrolling bomb middle in the length direction of the patrolling bomb, and one end of the reset spring is connected with the inner wall, close to the patrolling bomb head, of the patrolling bomb middle. The other end of the front locking assembly is rotationally connected with the missile wing assembly, and the other end of the front locking assembly is connected with the missile wing assembly; through the design of the reset spring and the brake locking mechanism, the missile wing assembly can be rapidly switched between the storage state and the pop-up state; the missile wing assemblies are stored before launching, so that the overall size of the patrolling missile is reduced, and transportation, storage and launching are facilitated; according to different task requirements, the rotating speed of the motor and the working state of the propeller can be flexibly adjusted, so that the flying speed, height and posture of the patrolling bomb are changed, tasks and functions of a traditional patrolling bomb can be completed, and the maneuverability and survivability of the patrolling bomb can be greatly improved.

The present application relates to the field of folding unmanned aerial vehicle structure, especially to a folding cruise missile with redundant locking and interference prevention wing unfolding structure, comprising a fuselage, a front wing structure, a rear wing structure, a vertical tail structure, a power system and an on-board device; the front wing structure is connected with the fuselage through a threaded nut, the rear wing structure is connected with the fuselage through a bearing seat cooperating with bolts, the vertical tail structure is connected with the fuselage through bolts, and the on-board device is fixed in the fuselage through bolts or adhesive bonding; before the cruise missile is launched, the wings are folded and attached to the surface of the fuselage, after the launch, the front wing structure and the rear wing structure are unfolded simultaneously until locked, when the rear wing structure is unfolded to the position, the vertical tail structure starts to unfold until locked. The present application has a double-redundant wing locking structure, and has a structure for preventing the front and rear wing structures and the vertical tail structure from interfering with each other during unfolding, which can effectively improve the success rate and stability of the folding cruise missile in the cylindrical launching, and has the advantages of simple and compact structure.

Unmanned aerial vehicle characterized in that one or more (fully) automatic firearms are mounted in a fixed-wing carrier drone for the purpose of combating other drones or cruise missiles.

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.

The present invention relates to a technology based on time coordination and belongs to the field of guidance technology. That is, the terminal guidance algorithm can perform time constraints to solve the problem of terminal cooperative strike. By decoupling the time constraint and the impact angle constraint, time control is realized in the lateral plane. And on this basis, taking the remaining time as the coordination variable, a cooperative terminal guidance strategy using a two-layer architecture is used to achieve the cooperative strike of multiple cruise missiles on the target. Thus, the problems of easily reducing the impact angle and time constraint control capabilities of the guidance algorithm and easily causing mutual interference between impact angle control and time control, which affect the miss distance, impact angle and time control accuracy, are solved.

The present invention discloses a distributed time-coordinated guidance method for a cruise missile cluster with limited control input, which belongs to the technical field of cruise missile cluster guidance and control. A two-layer cooperative guidance architecture for a cruise missile cluster is established; individuals use the estimated value of remaining flight time as a coordination variable, and exchange their respective estimated values ​​of remaining flight time through inter-missile communication. The coordination variable value expected by each missile is calculated by the coordination strategy and used as the input of the lower-layer time-constrained guidance law; the lower-layer time-constrained guidance law is decomposed into the lateral and longitudinal planes, and the attitude angle and throttle are calculated through the segmented guidance law, which are input into the autopilot as guidance control quantities; the steering amount and throttle amount are obtained according to the input attitude angle and throttle instructions, and the attitude and speed of the cruise missile are controlled to achieve time coordination. The present invention provides a distributed time-coordinated guidance method for a cruise missile cluster with limited control input to solve the problem of simultaneous attack of a cruise missile cluster on a stationary target on the ground when the control input is limited to attitude angle and throttle.

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

The present application relates to the technical field of unmanned aerial vehicle, and specifically provides a kind of based on tail seat vertical unmanned aerial vehicle cruise missile flight path planning and control method. Including: clear cruise missile flight space and flight path representation method;Through the sensor element of the cruise missile, real-time sensing cruise missile body position, geographical environment, obstacle position, enemy monitoring area three-dimensional space gridding, determine monitoring range;Determine the flight route algorithm of non-enemy monitoring area: apply fuzzy artificial potential field method to optimize the flight route of cruise missile;Based on fuzzy artificial potential field method, real-time calculation cruise missile desired flight route;Determine the flight route algorithm of enemy monitoring area: apply genetic algorithm to determine termination node and flight route;Cruise missile executes tracking, attack or return task according to the obtained flight route algorithm. Advantage lies in: it is beneficial to real-time optimization flight route of cruise missile;Flexible switching flight mode, without the aid of launching device;Task execution process is more controllable.

The invention relates to a low-delay high-definition image processing transmission method and system for a patrolling ammunition, and belongs to the technical field of patrolling ammunition-carried image processing and transmission, and the processing transmission method comprises the steps: obtaining multispectral image data synchronously collected by a visible light sensor and an infrared sensor carried by the patrolling ammunition; performing motion vector calculation and temperature feature extraction on the multispectral image data, and outputting a pixel-level value weight matrix; performing differential coding processing on the multispectral image data to generate a layered compressed data stream; the signal-to-noise ratio of a communication channel is measured in real time, the missile-target distance is solved, the residual electric quantity of the patrol missile is monitored, and a channel state parameter vector is output; querying a preset transmission decision table based on the channel state parameter vector and the hierarchical compressed data stream, and generating a transmission strategy instruction set; and according to the transmission strategy instruction set, performing frequency hopping packaging operation on the layered compressed data stream, and outputting an anti-interference data packet to a ground end. According to the invention, intelligent processing and reliable transmission of the image information of the patrolling bomb platform can be realized.

The invention relates to the technical field of intelligent ammunition, and discloses a non-aiming intelligent patrolling ammunition which comprises an induction part and a warhead part. The inducing part comprises a first flying mechanism, a plurality of controllable connecting mechanisms evenly connected to the first flying mechanism and a flue generating mechanism detachably connected to the controllable connecting mechanisms, and the first flying mechanism is used for driving the controllable connecting mechanisms and the flue generating mechanism to move along a set track; the flue generation mechanism is used for generating a flue along a set track; the induction part is additionally arranged on the warhead, when the target hitting command is executed, the induction part is separated from the warhead and forms the covering flue on the hitting flight track of the warhead, the specific position of the warhead in the view of an enemy can be effectively shielded, and therefore the risk that the warhead is hit down can be effectively reduced; and meanwhile, the induction part can intercept the attack of the enemy for the warhead, so that the striking success rate of the warhead is further improved.

The invention discloses a target comprehensive identification method based on a mixed information fusion model. The method comprises the following steps: acquiring original information collected by multiple types of sensors; the multiple types of sensors support radar sensors, photoelectric sensors and electric detection sensors; performing mixed information fusion on the original information, and processing the original information into fusion information Df; converting the fusion information Df into target time sequence data through time accumulation window processing; loading the target comprehensive recognition model, inputting target time sequence data to the target comprehensive recognition model, and obtaining a target recognition result; wherein the structure of the target comprehensive identification model adopts an FTTransformer without a LayerNorm layer, and the real category labels of the samples of the target comprehensive identification model comprise a miniature / light and small rotor unmanned aerial vehicle, a miniature / light and small fixed-wing unmanned aerial vehicle, a bird and a patrolling bomb. According to the technical scheme, the model can learn the high-dimensional representation of the sensor information, the data value is fully mined, and the recognition capability of the model on the unmanned aerial vehicle target is improved.

The application discloses a cruise missile barrel launching method and system. When the axial acceleration is greater than a set acceleration, a time period is delayed, and the missile body is completely out of the barrel and the missile wing is completely unfolded. In the attitude stabilization stage, the deflection of the missile body rudder surface is controlled to correct the flight attitude while the control motor provides thrust and speed until the flight attitude reaches the expected stable state. Through the control of the motor and the rudder surface, the disturbance caused by the out-of-barrel instantaneous impact force and the missile wing unfolding is overcome, the whole missile attitude is ensured to be in a stable range, the missile body is in a non-instability state, the influence of the disturbance is overcome, and the cruise missile instability and falling are avoided.

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 utility model provides a single-side beam type multifunctional operation storage and transportation frame for a high-speed unmanned aerial vehicle. The single-side beam type multifunctional operation storage and transportation frame comprises an operation frame, a height adjusting mechanism, a plurality of weighing assemblies and two bracket assemblies. A plurality of walking wheels are arranged at the bottom of the operation frame, the two bracket assemblies are arranged on the two sides of the operation frame correspondingly, the bracket assemblies are used for supporting a single-side beam of the high-speed unmanned aerial vehicle, the bracket assemblies are arranged on the operation frame in a liftable mode, and the height adjusting mechanism is in driving connection with the bracket assemblies. The weighing assembly is arranged on the operation frame. The single-side beam type multifunctional operation storage and transportation frame for the high-speed unmanned aerial vehicle can be convenient for workers to carry out operations such as storage, transportation, loading, operation and weighing of the single-side beam of the high-speed unmanned aerial vehicle, and is simple in overall structure, convenient to operate, low in manufacturing cost, high in man-machine efficiency and high in practicability. The unmanned aerial vehicle is suitable for storage, transportation and operation requirements of high-speed unmanned aerial vehicles below 600kg on conventional layout, rocket type layout, cruise missile type layout and the like of unmanned aerial vehicles.

The invention discloses a grating type multi-weapon node air-drop tray system which comprises weapon nodes, an air-drop tray frame, an industrial computer system, a mark point posture / position sensor, an electromagnetic release mechanism, an explosive release mechanism and the like. According to the air-drop tray system, sensor signals of mark points are received in real time through an industrial computer, the starting moment of stable falling of a tray is accurately judged, a node release program with an electromagnetic release mode and an initiating explosive release mode is triggered, and weapon nodes are sequentially dropped. The multi-node carrying tray is provided for striking weapons such as cruise missiles or air-drop torpedoes, the multi-node carrying tray is matched with a parachute system to work, a transport plane can be converted into a remote striking platform from a traditional material delivery platform, rapid deployment of a large number of weapon nodes is achieved at low cost, efficient striking is conducted on a target area, and the service life of the transport plane is prolonged. And the missile deployment capability and strategic response efficiency of the air force are remarkably improved.

The application discloses a midcourse guidance method of a loitering munition with space-time constraints and belongs to the field of guidance control. The application realizes the method as follows: constructing a midcourse guidance problem, planning expected midcourse guidance track points according to the midcourse guidance problem by using the computing resources of a launch platform before launching; adopting a Douglas-Puck algorithm to thin out the track points planned by the launch platform, and binding the extracted track points containing position, expected incident angle and arrival time information to a guidance control module of the loitering munition; taking an incident angle constraint guidance law as a benchmark guidance law, estimating the residual flight time of the loitering munition adopting the benchmark guidance law; designing a bias term to the control arrival time by using the residual flight time estimation value, constructing an incident angle and arrival time constraint guidance law by using the benchmark guidance law and the bias term; and according to the incident angle and arrival time constraint guidance law, the loitering munition sequentially passes through the bound midcourse guidance expected track points, so that the midcourse guidance of the loitering munition in a loitering segment is realized.

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.

1. The name of the product of this design: coaxial drone. 2. Purpose of this design product: The coaxial drone is a small cruise missile used in urban warfare. 3. The design key point of this appearance design product lies in the shape. 4. The picture or photo that best illustrates the design points: three-dimensional picture.