Portable variable-speed outburst anti-patrolling bomb

Abstract

The invention discloses a portable variable-speed outburst anti-patrolling bomb which comprises a patrolling bomb body, a bomb support, a boosting engine and a launch canister. The patrolling bomb is folded in the launching cylinder before being launched; the missile support is used for wrapping the patrol missile in a folded state; the launch canister is used for starting the boosting engine to push the patrolling bomb and the bomb support out of the launch canister and the remote controller; two power systems, namely a defense penetration rocket engine and a propeller, are arranged on the patrolling bomb, so that switching from patrolling to defense penetration can be performed, the capability of accelerating defense penetration of the patrolling bomb at the tail section of a trajectory through the defense penetration rocket engine is realized, and the probability that the patrolling bomb is intercepted by an enemy air defense system and an active defense system is reduced; the foldable structures of the main wings and the ailerons of the patrolling bomb are arranged, the launch canister is used for packaging under the cooperation of the bomb support, and the characteristics of being convenient to carry and launching in all terrains are achieved.

Description

TECHNICAL FIELD

[0001] The present application belongs to the technical field of cruise missiles, in particular to a portable variable-speed penetration cruise missile. BACKGROUND

[0002] A cruise missile is an intelligent ammunition with the ability of cruise reconnaissance and precision attack, which shows high tactical value in modern local conflicts and special operations. It is generally remotely controlled by an operator or autonomously searches, identifies and attacks targets, has long range and low cost, and is the preferred choice for attacking personnel and armored vehicles. At present, cruise missiles are mainly divided into two types according to size: individual cruise missiles and large vehicle-mounted cruise missiles. Among them, individual cruise missiles are carried by one or more personnel and can be launched in battlefield environments such as jungles and mountains where vehicles cannot enter, and have strong mobility and low logistics transportation requirements for ammunition.

[0003] The existing individual cruise missile mainly uses an electric motor to drive a propeller as the flight power. The flight speed of this power mode is generally slow, and in the penetration process, it is easy to be intercepted by the active defense system or short-range air defense system such as high-velocity machine guns of enemy targets, and the survival ability needs to be improved. On the contrary, individual anti-tank missiles and individual rocket missiles use rocket engines as propulsion power, which are high-speed and not easy to be intercepted by air defense systems, but have short range and cannot realize the characteristics of long-distance "cruise". At the same time, in order to realize the cruise capability, the individual cruise missile usually adopts a fixed wing or rotor layout, which increases the carrying difficulty of the operator and has a certain damage risk during carrying. SUMMARY

[0004] The purpose of the present application is to provide a portable variable-speed penetration cruise missile with the characteristics of long-range cruise, variable-speed penetration and easy to carry, to solve the problems existing in the prior art, improve the attack capability of the cruise missile on various advanced targets, reduce the probability of the cruise missile being intercepted, and reduce the carrying difficulty of the cruise missile.

[0005] The technical solution for achieving the purpose of the present application is as follows: A portable variable-speed penetration cruise missile, comprising a cruise missile, a missile holder, a boost engine and a launch tube; the cruise missile is folded and stored in the launch tube before launching; the missile holder is used to wrap the cruise missile in a folded state; the launch tube is used to start the boost engine to push the cruise missile and the missile holder out of the launch tube; It also includes a remote controller for controlling the flight attitude of the cruise missile; The cruise missile comprises: a missile body for carrying a main wing, an aileron, a rudder, a penetration rocket engine, an electric motor, a battery, a rudder, an inertial navigation device and a missile-borne computer; a battery for powering the cruise missile; The warhead is arranged at the front of the body of the missile, and is used for forming a jet to attack the target after explosion. The detection unit is arranged at the front of the warhead, and is used for detecting the distance between the missile and the target. The inertial navigation device is used for inertial navigation and assisting in calculating the flight attitude. The plurality of rudders are arranged at the rear of the body of the missile at equal intervals, and are controlled by the rudder to change the flight direction of the cruise missile. The pair of main wings and the pair of auxiliary wings are arranged at the two sides of the body of the missile, and are used for providing lift for the cruise missile when flying, the main wings and the auxiliary wings can be folded at the two sides of the body of the missile, the auxiliary wings are parallel to the main wings when being folded, and are used for supporting the main wings after being unfolded. The propeller is inserted at the rear end of the propeller shaft, and is used for rotating to provide power for the cruise missile in the cruising stage. The propeller shaft passes through the penetration rocket engine and is connected with the electric motor, and transmits the power of the electric motor to the propeller. The penetration rocket engine is used for providing power for the cruise missile when penetrating, and generates gas to blow the propeller away from the propeller shaft.

[0006] The missile-borne computer is used for calculating the flight attitude of the cruise missile, controlling the working of the rudder, the electric motor and the penetration rocket engine, and realizing the signal transmission and reception between the signal transmitter and the remote controller, when the distance between the missile and the target is less than a set value, the penetration rocket engine is started to provide a larger thrust to the cruise missile for penetration.

[0007] Compared with the prior art, the present application has the following advantages: (1) The present application provides a variable-speed penetration cruise missile capable of switching power modes, under the control of the remote controller, when approaching the target, the cruise missile can realize the power switching from the propeller propulsion to the rocket engine propulsion through the cooperation of the propeller, the propeller shaft, the electric motor and the penetration rocket engine, so as to realize variable-speed penetration and reduce the probability of being intercepted by the active defense system and the air defense system of the target, and realize long-distance and efficient attack under the cooperation of the warhead.

[0008] (2) The present application provides a portable and launchable cruise missile through the arrangement of the cruise missile, the four-piece missile carrier, the boost engine, the launching barrel and the remote controller, the lift structure of the cruise missile can be folded to facilitate the packaging of the cruise missile in the launching barrel, the cruise missile can meet the advantages of being foldable and portable for soldiers through the cooperation of the four-piece missile carrier and the launching barrel, and can realize barrel launching through the cooperation of the launching barrel and the boost engine, and can meet the functions of all-terrain launching and long-distance cruising. BRIEF DESCRIPTION OF DRAWINGS

[0009] In order to more clearly illustrate the technical solutions in the embodiments of the present application or the prior art, the following will briefly introduce the drawings needed in the embodiments. Obviously, the drawings described below only show some embodiments of the present application, and other drawings can also be obtained by those skilled in the art based on these drawings.

[0010] Figure 1 A general structural diagram of a portable variable-speed penetration cruise missile provided by the embodiment of the present application is shown in the figure. Figure 2 An assembly schematic diagram provided by the embodiment of the present application is shown in the figure. Figure 3 An external structural diagram of a cruise missile provided by the embodiment of the present application is shown in the figure. Figure 4 A detail structural diagram of A provided by the embodiment of the present application is shown in the figure. Figure 3 A detail structural diagram of A provided by the embodiment of the present application is shown in the figure. Figure 5 A sectional view of a cruise missile provided by the embodiment of the present application is shown in the figure. Figure 6 A detail structural diagram of B provided by the embodiment of the present application is shown in the figure. Figure 5 A detail structural diagram of B provided by the embodiment of the present application is shown in the figure. Figure 7 An unfolding and folding state diagram of a cruise missile provided by the embodiment of the present application is shown in the figure. Figure 8 A schematic diagram of a remote controller provided by the embodiment of the present application is shown in the figure.

[0011] Reference signs: 1, cruise missile; 101, camera; 102, warhead; 103, main wing; 1031, slot; 104, aileron; 105, missile body; 106, torsional spring; 107, rudder; 108, rudder machine; 109, propeller; 1091, connecting hole; 110, propeller shaft; 1101, spline; 111, penetration rocket engine; 1111, combustion chamber shell; 1112, baffle plate; 1113, propellant; 1114, bearing; 1115, nozzle; 1116, penetration engine ignition device; 112, electric motor; 113, battery; 114, missile-borne computer; 115, signal transmitter; 116, inertial navigation device; 117, wire; 118, stud; 2, missile support; 3, boost engine; 4, launching tube; 401, support; 402, trigger device; 403, boost engine ignition torch; 5, remote controller; 501, display screen; 502, control lever; 503, button; 504, signal receiving antenna; DETAILED DESCRIPTION

[0012] In order for those skilled in the art to better understand the technical solutions of the present application, the following will further introduce the present application in combination with the drawings. The following embodiments are used to illustrate the present application, but are not used to limit the scope of the present application.

[0013] As Figures 1 to 8 shown, the application provides a portable variable speed penetration cruise missile, comprising a cruise missile 1, four missile carriers 2, a boost engine 3, a launch tube 4 and a remote controller 5; the cruise missile 1 is folded into the launch tube 4 before launch for flight and attack on targets; the four missile carriers 2 are located outside the cruise missile 1; the boost engine 3 is located inside the launch tube 4 and is fixedly installed at the rear of the four missile carriers 2; the launch tube 4 is located outside the cruise missile 1, four missile carriers 2 and boost engine 3; the remote controller 5 is located outside the launch tube and is held by the operator.

[0014] Among them, the cruise missile 1 is used for flight and attack on targets; the four missile carriers 2 are used to wrap the cruise missile 1 in a folded state, so that it can move along the inner wall of the launch tube 4 when launched; the boost engine 3 is used to provide power when launching the cruise missile 1; the launch tube 4 is used to package for transportation and launch the cruise missile 1 for combat; the remote controller 5 is used to remotely control the flight direction of the cruise missile 1.

[0015] The application provides a portable variable speed penetration cruise missile by setting the cruise missile 1, four missile carriers 2, boost engine 3, launch tube 4 and remote controller 5, which can realize long-distance cruise under the condition of being foldable and convenient for soldiers to carry, and can realize all-terrain launch under the cooperation of the launch tube 3 and the boost engine 4. In addition, when the operator approaches the target through the remote controller 5, the cruise missile 1 can realize power switching through the cooperation of the propeller 109, the propeller shaft 110, the penetration rocket engine 111 and the electric motor 112, so as to realize variable speed penetration and reduce the probability of being intercepted by the target's active defense system and air defense system, and realize long-distance and efficient attack under the cooperation of the warhead 102.

[0016] Optionally, the cruise missile 1 comprises a camera 101, a warhead 102, a pair of main wings 103, a pair of ailerons 104, a body 105, two pairs of torsion springs 106, three rudders 107, three rudders 108, a propeller 109, a propeller shaft 110, a penetration rocket engine 111, an electric motor 112, a battery 113, a missile computer 114, a signal transmitter 115, an inertial navigation device 116, a plurality of wires 117, a plurality of studs 118; the camera 101 is installed at the front end of the cruise missile 1, used to shoot the situation in front of the cruise missile 1 when flying, and can detect the distance from the target, when the cruise missile 1 approaches the target less than a certain distance, the missile computer 114 judges the distance through the image data of the camera 101 and sends a power conversion signal to the penetration rocket engine 111; the warhead 102 is installed behind the camera 101 at the front of the cruise missile 1, and the warhead 102 explodes to form a metal jet to attack the target after the cruise missile 1 flies to the target; the body 105 has a threaded hole at the front end, which is threadedly connected with the rear part of the warhead 102, used to carry the main wings 103, ailerons 104, rudders 108, penetration rocket engine 111, electric motor 112, battery 113, missile computer 114 and other components; the pair of main wings 103 is installed on both sides of the body 105, used to provide main lift when the cruise missile 1 flies; the pair of ailerons 104 is installed on both sides of the body 105 and behind the main wings 103, the wing surface is parallel to the main wings 103 when folded, used to provide lift and support the main wings 103 when the cruise missile 1 flies; the two pairs of torsion springs 106 are respectively installed at the connection between the main wings 103 and ailerons 104 and the body 105, used to provide torque to deploy the main wings 103 and ailerons 104 after launching; the three rudders 107 are installed at equal intervals on the outside of the rear part of the body 105, connected with the rudders 108 through the light hole on the body 105, used to change the flight direction of the cruise missile 1; the rudders 108 are installed on the inside of the rear part of the body 105, fixed with the body 105 and connected with the rudders 107 through the light hole on the body 105, used to drive the rudders 107 to rotate.The propeller 109 is inserted into the rear end of the propeller shaft 110, which rotates at high speed to provide power for the cruise missile 1 during the cruising stage; the propeller shaft 110 is movably installed in the inner aperture of the penetration rocket engine 111, which is used to transmit the power of the electric motor 112 to the propeller 109; the penetration rocket engine 111 penetrates the propeller shaft 110 from the outside and is fixedly installed on the inner side of the rear part of the missile body 105, which is used to provide power for the penetration of the cruise missile 1; the electric motor 112 is installed in the front part of the penetration rocket engine 111, fixed with the missile body 105 through the stud 118, and connected with one end of the propeller shaft 110, which is used to drive the propeller shaft 110 to rotate; the battery 113 is fixed with the missile body 105 through the stud 118 and installed in the front part of the electric motor 112, electrically connected with other components requiring electricity through the wire 117; the missile-borne computer 114 is installed in the front part of the battery 113, which is used to process and calculate signals; the signal transmitter 115 is fixedly installed in the front part of the missile-borne computer 114 through the stud 118 and electrically connected with the missile-borne computer 114, which is used to transmit and receive signals between the signal transmitter 115 and the remote controller 5; the inertial navigation device 116 is fixedly installed in the front part of the missile body 105 through the stud 118, which is used for inertial navigation and auxiliary calculation of flight attitude.

[0017] Optionally, the missile body 102 is in the shape of a cylindrical shell as a whole and is provided with a plurality of threaded holes for connecting with the studs 118.

[0018] In a specific embodiment, a plurality of studs 118 are connected and fixed with the missile body 105 through a plurality of threaded holes opened in the upper and lower parts of the missile body 105, and each stud 118 is provided with a slot at the outer side end, which facilitates the production personnel to screw it into the threaded hole and tighten it.

[0019] In a specific embodiment, a plurality of wires 117 electrically connect the camera 101 with the missile-borne computer 114 and the signal transmitter 115 through the contacts of the respective electrical components, and transmit signals; and the plurality of wires 117 electrically connect the battery 113 with the camera 101, the inertial navigation device 116, the signal transmitter 115, the missile-borne computer 114, the rudder 108 and the electric motor 112 through the contacts of the respective electrical components, and provide electric current.

[0020] Optionally, the missile body 105 is provided with a pair of protrusions on the front part of both sides, which are used to install the torsional spring 106 and hingedly connect the main wing 103; the missile body 105 is provided with a pair of protrusions on the rear part of both sides, which are used to install the torsional spring 106 and hingedly connect the aileron 104; the torsional spring 106 is used to provide the force for the expansion of the main wing 103 and the aileron 104 after the launch of the cruise missile 1.

[0021] Optionally, a slot 1031 is formed below the main wing 103, and the auxiliary wing 104 is connected to the main wing 103 through the slot 1031. When the cruise missile 1 is deployed, the connection between the auxiliary wing 104 and the main wing 103 slides along the slot 1031 to the wing tip of the main wing 103.

[0022] In the specific embodiment, the upper end of the auxiliary wing 104 is connected to the slot 1031 through a cylindrical protrusion, which allows the auxiliary wing 104 to slide freely along the slot 1031. Before deployment, the main wing 103 and the auxiliary wing 104 are substantially parallel. After the cruise missile 1 is launched, the main wing 103 and the auxiliary wing 104 are fully deployed under the action of the torsion spring 106. The cylindrical protrusion at the upper end of the auxiliary wing 104 is located at the outer end of the slot 1031, and the angle between the auxiliary wing 104 and the main wing 103 is close to a right angle. At this time, the main wing 103, the auxiliary wing 104, and the body 105 form a stable structure under the combined action of the torsion spring 106 and the air force, providing lift for the flight of the cruise missile 1.

[0023] Optionally, the propeller and the propeller shaft 110 are fixed by interference fit through the spline 1101 and the connecting hole 1091. The depth of the connecting hole 1091 is equal to the length of the spline 1101. When the cruise missile 1 is cruising, the propeller shaft 110 drives the propeller to rotate through the spline 1101. When the cruise missile 1 is penetrating defense, since the propeller is only subjected to a small restraining force in the direction away from the flight direction of the cruise missile 1, the high-speed gas ejected by the penetration rocket engine 111 can directly blow the propeller away from the propeller shaft 110, avoiding interference of the propeller with the penetration rocket engine 111.

[0024] Optionally, the penetration rocket engine 111 comprises a combustion chamber shell 1111, two propellant blocking plates 1112, propellant 1113, bearing 1114, nozzle 1115, penetration engine ignition device 1116; the combustion chamber shell 1111 is fixedly installed at the rear of the projectile body, providing space for the combustion of the propellant 1113, and its axis is a hollow straight pipe, which can introduce external space into the center of the combustion chamber shell 1111, for movably installing the propeller shaft 110 and isolating it from the interior space of the combustion chamber shell 1111 and the propellant 1113; the two propellant blocking plates 1112 are fixedly installed at the front and rear ends of the interior of the combustion chamber shell 1111, for fixing the propellant 1113; the propellant 1113 is located in the combustion chamber shell 1111 and is fixed by the two propellant blocking plates 1112, concentrically installed with the combustion chamber shell 1111, for generating high-temperature and high-pressure gas by combustion in the penetration section, providing thrust for the penetration engine; the bearing 1114 is installed in the hollow straight pipe at the axis of the combustion chamber shell 1111, close to the nozzle 1115, for bearing the propeller shaft 110 to enable it to rotate freely in the hollow straight pipe at the axis of the combustion chamber shell 1111; the nozzle 1115 is located at the rear end of the combustion chamber shell 1111, fixedly connected with the combustion chamber shell 1111 by threads, for accelerating the ejection speed of the gas generated by the combustion of the propellant 1113, increasing the thrust; the penetration rocket engine ignition device 1116 is fixedly installed between the propellant 1113 and the combustion chamber shell 1111, for igniting the propellant 1113 when the cruise missile 1 penetrates.

[0025] In the specific embodiment, the bearing 1114 is a plastic rolling bearing, the outer ring of the bearing 1114 is fixedly installed with the inner wall of the hollow straight pipe at the axis of the combustion chamber shell 1111, and the inner ring of the bearing 1114 is fixedly installed with the propeller shaft 110, when the motor drives the propeller shaft 110 to rotate, one end of the propeller shaft 110 is constrained by the motor and the other end is constrained by the bearing 1114, only allowing fixed-axis rotation and not directly contacting the combustion chamber shell 1111, preventing heat generated by high-speed rotation friction from igniting the propellant 1113; in addition, the gap between the inner wall of the hollow straight pipe at the axis of the combustion chamber shell 1111 and the propeller shaft 110 can be filled with lubricating grease, further reducing friction caused by installation errors.

[0026] Optionally, the four pieces of the projectile support 2 are made of plastic material, the internal shape matches the cruise missile 1, and the outer diameter after splicing can match the inner diameter gap of the launch tube 4; after splicing, the outer diameter of the four pieces of the projectile support 2 can match the inner diameter gap of the launch tube 4; after splicing, the rear end of the four pieces of the projectile support 2 forms a cylindrical groove, for fixedly installing the boost engine 3.

[0027] In the specific embodiment, the boost engine 3 is a solid rocket engine, the engine shell is an aluminum alloy, and the propellant burns fast during launching and is burned out before the missile flies out of the launching barrel 4.

[0028] Optionally, the launching barrel 4 comprises a support 401, a trigger device 402 and a boost engine ignition torch 403; the support 401 is movably installed at the lower front end of the launching barrel 4 and can be unfolded as a support during launching; the trigger device 402 is used for triggering the boost engine ignition torch 403 by the operator during launching; and the boost engine ignition torch 403 is used for starting the boost engine 3.

[0029] Optionally, the remote controller 5 comprises a display screen 501, a control lever 502, a button 503 and a signal receiving antenna 504; the display screen 501 is located at the upper part of the remote controller 5 and is used for displaying the real-time picture taken by the camera 101; the control lever 502 is used for conveniently controlling the flight attitude of the flying bomb 1 by the operator; the button 503 is used for turning on the remote controller 5; and the signal receiving antenna 504 is used for transmitting signals with the flying bomb 1.

[0030] In the present application, the launching process of the flying bomb 1 is as follows: when the flying bomb 1 needs to be launched, first, unfold the support 401 to support the launching barrel 4, so that the front opening of the launching barrel 4 is directed obliquely upward; then, the operator pulls down the trigger device 402 to ignite the boost engine ignition torch 403, starts the boost engine 3, and the boost engine 3 works to push the flying bomb 1 in the folded state wrapped by the four bomb carriers 2 out of the launching barrel 4 and provides a high initial speed. After the flying bomb 1 is pushed out of the launching barrel 4, the boost engine 3 stops working, the four bomb carriers 2 and the boost engine 3 are separated under the action of air force, the main wing 103 and the aileron 104 of the flying bomb 1 are unfolded under the action of the torque of the torsion spring 106, at the same time, the bomb-borne computer 114 is activated and sends an instruction to the electric motor 112 through the wire 117, the electric motor 112 works to drive the propeller to rotate at a high speed through the propeller shaft 110, thereby providing power for the flying of the flying bomb 1, and the flying bomb 1 enters the flying stage.

[0031] In the present application, the control process of the flying bomb 1 is as follows: when the flying bomb 1 is flying, the camera 101 transmits the real-time picture taken to the signal transmitter 115, the signal transmitter 115 projects the picture signal on the display screen 501 of the remote controller 5 through the signal receiving antenna 504, the operator adjusts the flight direction and attitude according to the picture by moving the control lever 502, the signal is transmitted to the signal transmitter 115 on the flying bomb 1 after being emitted by the signal receiving antenna 504 on the remote controller 5, the signal transmitter 115 transmits the signal to the rudder 108 after being analyzed by the bomb-borne computer 114 through the wire 117, the rudder 108 drives the rudder blade 107 to rotate, changes the aerodynamic shape of the flying bomb 1, and makes the flight direction and attitude of the flying bomb 1 change.

[0032] Wherein, when the signal between the cruise missile 1 and the remote controller 5 is lost or poor, the inertial navigation device 116 works to maintain the cruise missile 1 to fly steadily forward.

[0033] In the application, the variable speed penetration process of the cruise missile 1 is as follows: when the cruise missile 1 approaches the target within a range of hundreds of meters, the camera 101 locks the target and detects the distance to the target, when the distance between the missile and the target is less than a set value, the camera 101 transmits the signal to the penetration engine ignition device 1116 through the wire 117 by the missile-borne computer 114, the penetration engine ignition device 1116 ignites the propellant 1113, the penetration rocket engine 111 starts to work, the high-speed gas burned and sprayed by the propellant 1113 is added to supersonic speed through the nozzle 1115, the propeller is blown away from the propeller shaft 110, avoiding causing the thrust eccentricity, at the same time, the thrust gives the cruise missile 1 a larger acceleration, so that it continuously accelerates to the target, reduces the probability of being intercepted, and increases the penetration ability.

[0034] In summary, the portable variable speed penetration cruise missile provided by the application can realize long-distance cruising and the function of reducing the probability of being intercepted in the terminal penetration under the conditions of meeting the foldable and convenient for soldiers to carry.

[0035] The embodiment provides a cruise missile which can realize long-distance cruising and variable speed penetration, can be folded and is convenient to carry, realizes long-distance precision guidance attack on the target outside the target defense area of the enemy by a single soldier, and realizes the ability of the cruise missile to accelerate and penetrate in the terminal trajectory by the penetration rocket engine, reduces the probability of being intercepted by the enemy air defense system and active defense system, and increases the hit probability; in addition, the foldable structure of the main wing and the auxiliary wing of the cruise missile is arranged, the launching cylinder is encapsulated under the cooperation of the missile support, and the characteristics of convenient carrying and all-terrain launching are realized.

[0036] The above only describes some exemplary embodiments of the application by way of illustration, without doubt, for ordinary skilled in the art, the described embodiments can be modified in various ways without departing from the spirit and scope of the application. Therefore, the above figures and description are illustrative in nature and should not be understood as limiting the scope of protection of the claims of the application.

Claims

1. A portable variable-speed penetration cruise missile, comprising a cruise missile, a missile carrier, a boost engine and a launching tube; the cruise missile is folded in the launching tube before launching; the missile carrier is used to wrap the cruise missile in the folded state; the launching tube is used to start the boost engine to push the cruise missile and the missile carrier out of the launching tube; characterized in that, it further comprises a remote controller for controlling the flight attitude of the cruise missile; the cruise missile comprises: a missile body for carrying a main wing, an auxiliary wing, a rudder, a penetration rocket engine, an electric motor, a battery, a rudder, an inertial navigation device and a missile-borne computer; the battery is used to power the cruise missile; a warhead is arranged at the front of the missile body for forming a jet to attack the target after detonation; a detection unit is arranged at the front of the warhead for detecting the distance between the missile and the target; the inertial navigation device is used for inertial navigation and assists in calculating the flight attitude; a plurality of rudders are arranged at the rear of the missile body at equal intervals on the outside, and the flight direction of the cruise missile is changed by controlling the rudders; a pair of main wings and a pair of auxiliary wings are arranged on both sides of the missile body for providing lift for the cruise missile during flight, the main wings and the auxiliary wings can be folded on both sides of the missile body, the auxiliary wings are parallel to the main wings when folded, and are used to support the main wings after being unfolded; a propeller is inserted into the rear end of the propeller shaft for rotating to provide power for the cruise missile during the cruise stage; a propeller shaft passes through the penetration rocket engine and is connected with the electric motor to transmit the power of the electric motor to the propeller; the penetration rocket engine is used to provide power for the cruise missile during penetration, and generates gas to blow the propeller away from the propeller shaft; the missile-borne computer is used to calculate the flight attitude of the cruise missile, control the operation of the rudder, the electric motor and the penetration rocket engine, and realize signal transmission and reception between the remote controller and the missile-borne computer through a signal transmitter; when the distance between the missile and the target is less than a set value, the penetration rocket engine is started to provide greater thrust to the cruise missile for penetration. The penetration rocket engine comprises a combustion chamber shell, two propellant blocking plates, a propellant, a bearing, a nozzle and a penetration engine ignition device; the combustion chamber shell is fixedly installed in the missile body, a hollow straight pipe is arranged at the axis of the combustion chamber shell for installing the propeller shaft and isolating the propeller shaft from the interior space of the combustion chamber shell and the propellant; the two propellant blocking plates are fixedly installed at the front and rear ends of the combustion chamber shell for fixing the propellant; the bearing is installed in the hollow straight pipe close to the nozzle for bearing the propeller shaft to enable it to rotate freely in the hollow straight pipe; the nozzle is fixedly installed at the rear end of the combustion chamber shell for accelerating the ejection speed of the gas generated by the combustion of the propellant; the penetration engine ignition device is fixedly installed between the propellant and the combustion chamber shell for igniting the propellant when the cruise missile penetrates. The propeller and the propeller shaft are inserted and fixed by interference fit of splines and connecting holes, and the depth of the connecting hole is equal to the length of the spline. A one-slot groove is opened below the main wing, and the upper end of the auxiliary wing is gap-fitted with the one-slot groove through a cylindrical protrusion, so that the auxiliary wing can slide freely along the one-slot groove; after the cruise missile is launched, the main wing and the auxiliary wing are completely unfolded under the action of the torsion spring, and the cylindrical protrusion at the upper end of the auxiliary wing abuts against one end outside the one-slot groove. ​ ​ ​ ​ ​ ​ ​ ​ ​ ​ 2. The portable variable speed penetration cruise missile of claim 1, wherein, ​ 3. The portable variable speed penetration cruise missile of claim 1, wherein, ​ 4. The portable variable speed penetration cruise missile of claim 1, wherein, ​ 5. The portable variable speed penetration cruise missile of claim 1, wherein, The four elastic supports are spliced to match the inner diameter of the launching tube, and the rear end of the spliced elastic supports is formed with a cylindrical groove for fixing the boost engine.

6. The portable variable-speed penetration cruise missile of claim 1, wherein, The launching tube comprises a support, a trigger device and a boost engine torch; the support is movably installed at the lower front end of the launching tube and can be unfolded as a support during launching; the trigger device is used to trigger the boost engine torch during launching; and the boost engine torch is used to start the boost engine.

7. The portable variable-speed penetration cruise missile of claim 1, wherein, The front part of the body of the missile is provided with a pair of protrusions for installing torsion springs and hingedly connecting main wings; and the rear part of the body of the missile is provided with a pair of protrusions for installing torsion springs and hingedly connecting ailerons.

8. The portable variable speed penetration cruise missile of claim 1, wherein, The detection unit adopts a camera; and the remote controller comprises a display screen, a control lever, buttons and a signal receiving antenna. The display screen is located at the upper part of the remote controller and is used to display the real-time picture taken by the camera; the control lever is used to control the flight attitude of the flying bomb; and the buttons are used to turn on the remote controller. The signal receiving antenna is used to transmit signals with the flying bomb.

Images