Flying bomb with variable aerodynamic configuration

Abstract

The utility model provides a variable aerodynamic configuration patrolling bomb, including bomb body, two bomb wings and two rudder wings, the bomb wings are connected with bomb body front part through bomb wing unfolding mechanism so as to make the bomb wings fold back to the bomb body lengthways, the bomb wings include outer wing and inner wing, the rudder wings are connected with the bomb body front part through the outer wing and the inner wing, and the rudder wings are connected with the bomb body front part through the rudder wings. The outer wing and the inner wing are telescopically connected through a missile wing telescopic mechanism, and the rudder wing is connected with the rear portion of the missile body through a rudder wing unfolding mechanism so that the rudder wing can be folded forwards and longitudinally to the missile body. According to the utility model, the missile wings and the rudder wings are designed to be foldable and can be conveniently folded and placed in the launch canister before launching, and meanwhile, the missile wings are designed to be in a telescopic structural form and can be stretched into different lengths according to the flight environment and combat mission requirements, so that the span-chord ratio of the missile wings is adjusted, and the aerodynamic shape of the patrolling missile is changed; the unmanned aerial vehicle has the advantages of long patrol flight time, long combat distance, wide speed range and high cruise height.

Description

TECHNICAL FIELD

[0001] The utility model belongs to the field of the aerodynamic shape of the cruise missile, specifically relates to a variable aerodynamic shape cruise missile. BACKGROUND

[0002] The cruise missile is the intelligent missile between the cruise missile and the unmanned plane, and the main tactical and technical performances of the cruise missile include the cruise time, the combat distance, the speed range and the cruise height, and the high-performance tactical index brings the challenge to the overall design of the cruise missile, and the existing fixed shape cruise missile cannot meet such wide speed range and airspace. CONTENT OF THE UTILITY MODEL

[0003] The utility model aims at providing a variable aerodynamic shape cruise missile, and at least can solve the partial defects in the prior art.

[0004] In order to achieve the above-mentioned purpose, the utility model adopts the following technical scheme:

[0005] A variable aerodynamic shape cruise missile, including the missile body, two wings and two rudders, the wing is connected with the front part of the missile body through the wing unfolding mechanism, so that the wing can be folded to the rear longitudinal missile body, the wing includes the outer wing and the inner wing, the outer wing and the inner wing are connected through the wing telescopic mechanism, the rudder is connected with the rear part of the missile body through the rudder unfolding mechanism, so that the rudder can be folded to the front longitudinal missile body.

[0006] Further, the included angle between the two wings is 0 degrees when the two wings are folded, and the included angle between the two wings is 180 degrees when the two wings are unfolded, and the two rudders are unfolded in the inverted V shape.

[0007] Further, the wing unfolding mechanism includes a fixed shaft, two tension springs and two connecting cranks, the fixed shaft is fixedly connected on the missile body, one end of two connecting cranks is connected with one end of two wings respectively, the other end of two connecting cranks is rotatably connected on the fixed shaft, one end of two tension springs is connected on two connecting cranks respectively, the other end of two tension springs is connected on the missile body.

[0008] Further, the axial section of the missile body corresponds the wing installation position and has the inclined surface that inclines downward along the direction from the front end to the rear end of the missile body, the installation recess is arranged on the inclined surface, and the wing unfolding mechanism is installed in the installation recess.

[0009] Further, the wing folding mechanism comprises a wing folding motor, a gear and a rack, the gear is connected to one end of the inner wing away from the body, and the rotation axis of the gear is perpendicular to the length direction of the inner wing, the gear is electrically connected with the wing folding motor, and the rack is installed on the inner side wall of the outer wing along the length direction of the outer wing and is in meshing connection with the gear.

[0010] Further, the wing folding mechanism further comprises a folding guide connecting piece in sliding connection between the folding guide connecting piece and the outer wing, and the rotation axis of the gear is fixedly connected with the folding guide connecting piece.

[0011] Further, the rudder wing unfolding mechanism comprises a rudder wing motor, a gear transmission assembly, a rudder wing main rotating shaft, a rudder wing unfolding rotating shaft and a rudder wing torsional spring, one end of the rudder wing unfolding rotating shaft is fixedly connected with the rudder wing, the other end of the rudder wing unfolding rotating shaft is connected with the rudder wing main rotating shaft through the rudder wing torsional spring, and the rudder wing motor is connected with the rudder wing main rotating shaft through the gear transmission assembly so as to drive the rudder wing main rotating shaft to rotate around its own axis.

[0012] Further, the gear transmission assembly comprises a rudder wing bevel gear one, a rudder wing bevel gear two, a rudder wing bevel gear shaft, a rudder wing half gear one and a rudder wing half gear two, the rudder wing bevel gear one is connected with the movable end of the rudder wing motor, the rudder wing half gear two is connected with the rudder wing main rotating shaft, the rudder wing bevel gear two and the rudder wing half gear one are coaxially connected with the rudder wing bevel gear shaft, and the rudder wing bevel gear two and the rudder wing half gear one are in meshing connection with the rudder wing bevel gear one and the rudder wing half gear two respectively.

[0013] Further, the end of the wing away from the body is provided with ailerons for controlling the rolling loading channel when the wing is unfolded.

[0014] Further, the body comprises a bullet head, a bullet body and a bullet tail, the bullet head is a suspended cabin type head, the bullet body is a non-circular section, and the bullet tail is contracted from front to back to be a stern shape.

[0015] Compared with the prior art, the beneficial effects of the utility model are as follows:

[0016] The wing and the rudder wing of the variable aerodynamic shape cruise flying bomb are both in a foldable form, are convenient to fold and placed in a launching barrel before launching, the wing is designed in a telescopic structure form, can be telescoped into different lengths according to the flight environment and combat task requirements, the wing aspect ratio is adjusted, the aerodynamic shape of the cruise flying bomb is changed, the cruise flying bomb has the advantages of long cruise time, long combat distance, wide speed range and high cruise height.

[0017] The utility model will be further described in detail below with reference to the drawings. DRAWINGS

[0018] Figure 1 is the state diagram of the variable aerodynamic shape cruise missile of the utility model in the state of being placed in the launching cylinder;

[0019] Figure 2 is the axial structure diagram of the variable aerodynamic shape cruise missile of the utility model;

[0020] Figure 3 is the circumferential arrangement diagram of the wing and the rudder wing of the variable aerodynamic shape cruise missile of the utility model;

[0021] Figure 4 is the diagram of the wing being stretched to the maximum state in the utility model;

[0022] Figure 5 is the diagram of the wing being contracted to the minimum state in the utility model;

[0023] Figure 6 is the wing profile diagram in the utility model;

[0024] Figure 7 is the structure diagram of the wing unfolding mechanism in the utility model;

[0025] Figure 8 is Figure 7 the sectional view along A-A;

[0026] Figure 9 is the connection diagram of the outer wing and the inner wing of the wing in the utility model;

[0027] Figure 10 is Figure 9 the enlarged view of I part;

[0028] Figure 11 is the diagram of the rudder wing being unfolded in the utility model;

[0029] Figure 12 is the wing profile diagram in the utility model;

[0030] Figure 13 is the structure diagram of the rudder wing unfolding mechanism in the utility model.

[0031] Explanation of reference signs: 1, launching tube; 2, projectile body; 3, wing; 4, rudder wing; 5, warhead; 6, wing unfolding mechanism; 7, mounting groove; 8, inclined surface; 9, rudder wing unfolding mechanism; 10, tail; 11, propeller; 12, integrated cabin section; 13, wing cabin section; 14, battery cabin section; 15, rudder cabin section; 16, inner wing; 17, outer wing; 18, tension spring; 19, connecting crank; 20, fixed shaft; 21, nut; 22, rack; 23, gear; 24, rotating shaft; 25, telescopic guide connecting piece; 26, wing telescopic motor; 27, rudder wing motor; 28, rudder wing bevel gear one; 29, rudder wing bevel gear two; 30, rudder wing bevel gear shaft; 31, rudder wing half gear one; 32, rudder wing half gear two; 33, rudder wing unfolding shaft; 34, rudder wing main rotating shaft; 35, rudder wing torsional spring. DETAILED DESCRIPTION

[0032] The technical solutions in the embodiments of the present application will be clearly and completely described below with reference to the drawings in the embodiments of the present application. Obviously, the described embodiments are only part of the embodiments of the present application, rather than all the embodiments. Based on the embodiments in the present application, all other embodiments obtained by those skilled in the art without creative work fall within the scope of protection of the present application.

[0033] In the description of the present application, it should be understood that the terms "center", "upper", "lower", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer" and the like indicate the orientation or positional relationship based on the orientation or positional relationship shown in the drawings, and are only for the convenience of describing the present application and simplifying the description, and therefore cannot be understood as indicating or implying that the device or element referred to must have a particular orientation, be constructed and operated in a particular orientation, and therefore cannot be understood as a limitation on the present application.

[0034] In the description of the present application, it should be noted that unless otherwise explicitly specified and limited, the terms "mounting", "connecting", "connection" should be understood broadly, for example, it can be fixed connection, or detachable connection, or abutting connection, or integrally connected; for those skilled in the art, the specific meaning of the above terms in the present application can be understood according to the specific circumstances.

[0035] The terms "first", "second" are only for descriptive purposes, and cannot be understood as indicating or implying relative importance or implicitly indicating the number of the indicated technical features. Therefore, the features limited by "first", "second" can explicitly or implicitly include one or more features; in the description of the present application, unless otherwise specified, the meaning of "multiple" is two or more.

[0036] AsFigures 1 to 13 As shown in the figure, the embodiment provides a variable aerodynamic configuration cruise missile, which comprises a missile body 2, two wings 3 and two rudders 4. The wings 3 are connected to the front of the missile body 2 through a wing unfolding mechanism 6, so that the wings 3 can be folded longitudinally rearward to the missile body 2. The wings 3 comprise outer wings 17 and inner wings 16, which are connected through a wing telescopic mechanism. The rudders 4 are connected to the rear of the missile body 2 through a rudder unfolding mechanism 9, so that the rudders 4 can be folded longitudinally forward to the missile body 2.

[0037] In the embodiment, before the cruise missile is launched, the wings 3 are folded and unfolded on the top of the missile body 2 through the wing unfolding mechanism 6, and the rudders 4 are folded and unfolded to the surface of the missile body 2 through the rudder unfolding mechanism 9. The folded cruise missile can be loaded into a launch tube 1. When launched, the cruise missile is pushed out of the launch tube 1 by external force to obtain a certain initial speed. After the cruise missile is pushed out of the launch tube 1, the wings 3 and the rudders 4 are unfolded through the wing unfolding mechanism 6 and the rudder unfolding mechanism 9. The unfolded wings 3 are used to generate lift to maintain the flight of the cruise missile in the air. The unfolded rudders 4 are used to adjust the stability of the whole missile, provide a control moment, and meet the requirements of maneuverability, stability and controllability. The wings 3 are designed as a telescopic structure, and the relative movement of the inner wings 16 and the outer wings 17 of the unfolded wings 3 can be adjusted through the wing telescopic mechanism to realize the telescoping of the wings 3 to different span lengths, so as to adjust the wing aspect ratio and change the aerodynamic configuration of the cruise missile to adapt to different flight environments and combat task requirements.

[0038] According to the change of the combat environment, for example, when flying at an altitude of 5km or above, the air is thin, the wings 3 can be extended to match the altitude and speed to achieve the optimal lift-drag ratio. When flying at an altitude of about 200m, the air density is high and the dynamic pressure head is large, the wings 3 can be retracted to match the altitude and speed to achieve the optimal lift-drag ratio, which guarantees the long endurance requirement of the cruise missile.

[0039] According to the intelligent transformation of the combat task, for example, when the exact position of the target is known, the wings 3 can be retracted to the appropriate position according to the energy condition of the cruise missile (to reach the target) to improve the flight speed and quickly reach the battlefield to complete the attack task. When the exact position of the target is unknown, the cruise missile is launched to the suspicious area, the wings 3 can be extended, the aspect ratio is increased, the lift of the whole missile is increased, at this time the propeller speed of the power system can be reduced, the flight speed can be reduced, the battery output power can be reduced, the hovering time can be increased, the area can be searched for a long time, and the target can be searched. After the target is found, the combat state is changed in time (the wings 3 are retracted), the maneuverability of the cruise missile is improved to attack the target and complete the attack task.

[0040] Specifically, as shown in the figure, Figure 2As shown, the body 2 includes a nose 5, a body and a tail 10, the nose 5 adopts a gondola seeker, providing a large field of view angle, improving the search capability of the loitering munition; the body adopts a non-circular cross section, maximizing the use of its internal space, improving the radius of the warhead, and improving the power of the warhead; the tail 10 is tapered from front to rear like a stern, which is beneficial to reduce drag and full missile mass parameter design, the tail 10 as the power cabin section of the body 2, the tail 10 tail is provided with a propeller 11, which provides power for the loitering munition, the propeller 11 adopts a foldable, two-blade fixed-wing pitch propeller. Among them, the body is sequentially from front to back a comprehensive cabin section 12, a wing cabin section 13, a battery cabin section 14, and a rudder cabin section 15, the wing 3 is arranged at the top of the wing cabin section 13, and the rudder wing 4 is arranged at the rudder cabin section 15.

[0041] Optionally, when the two wings 3 are in the retracted state, the included angle between the two wings 3 is 0 degrees, and when the two wings 3 are in the expanded state, the two wings 3 form a straight wing shape, that is, the included angle between the two wings 3 is 180 degrees; the planar shape of the wing 3 is various, such as Figure 6 As shown, this embodiment adopts a large aspect ratio, curved thick airfoil, such as NACA9509 airfoil. With the increase of the aspect ratio of the wing 3, the lift-drag ratio of the wing 3 increases, so that the airfoil is very suitable as the wing of a low-speed, long-endurance aircraft. However, the wing with large aspect ratio and thick airfoil is very unfavorable for high-speed flight. This embodiment fully utilizes the characteristics of low-speed large lift-drag ratio of the large aspect ratio wing 3 by adopting the deformable wing 3 design, and combines the deformable design of the wing 3 to control the extension or contraction of the wing 3 according to different external environments, adjust the aspect ratio of the wing 3, and thus achieve the purpose of changing the aerodynamic shape of the loitering munition. For example Figure 11 and Figure 12 As shown, the two rudder wings 4 are expanded in an inverted V shape to control the longitudinal and heading channels, and the rudder wing 4 adopts NACA0004 airfoil.

[0042] For the expansion and retraction of the wing 3, in some embodiments, such as Figure 4 , Figure 7 and Figure 8As shown, the wing unfolding mechanism 6 comprises a fixed shaft 20, two tension springs 18 and two connecting cranks 19. The fixed shaft 20 is vertically connected to the body 2. One end of each of the two connecting cranks 19 is connected to one end of each of the two wings 3. The other end of each of the two connecting cranks 19 is rotatably connected to the fixed shaft 20. The two connecting cranks 19 are arranged along the axial direction of the fixed shaft 20. Preferably, a nut 21 is arranged at the end of the fixed shaft 20 to limit the axial position of the two connecting cranks 19. One end of each of the two tension springs 18 is connected to one end of each of the two connecting cranks 19 close to the fixed shaft 20. The other end of each of the two tension springs 18 is connected to the body 2. The two tension springs 18 provide torsional force for the unfolding and folding of the two wings 3. When the cruise missile is loaded into the launching tube 1, the two wings 3 are folded back onto the body 2, and the two tension springs 18 are in a stretched state. The launching tube 1 constrains the two wings 3. When the cruise missile is launched out of the launching tube 1, the two connecting cranks 19 rotate around the fixed shaft 20 under the action of the two tension springs 18, thereby driving the two wings 3 to unfold.

[0043] For the telescopic implementation of the wings 3, in some embodiments, as shown in Figure 9 and Figure 10 the wing telescopic mechanism comprises a wing telescopic motor 26, a gear 23 and a rack 22. The gear 23 is connected to one end of the inner wing 16 away from the body 2, and the axis of the rotating shaft 24 of the gear 23 is perpendicular to the length direction of the inner wing 16. The gear 23 is electrically connected to the wing telescopic motor 26. The rack 22 is mounted on the inner side wall of the outer wing 17 along the length direction of the outer wing 17, and the rack 22 is in meshing connection with the gear 23. The wing telescopic motor 26 drives the gear 23 and the rack 22 to generate power, so that the outer wing 17 moves reciprocatingly relative to the inner wing 16, as shown in Figure 4 and Figure 5 thereby the wings 3 can be telescoped to different lengths to adjust the aspect ratio of the wings 3.

[0044] As shown in Figure 10 the wing telescopic mechanism further comprises a telescopic guide connecting piece 25. The telescopic guide connecting piece 25 is in sliding connection with the outer wing 17, and the reciprocating movement of the outer wing 17 is limited and guided by the telescopic guide connecting piece 25. The rotating shaft 24 of the gear 23 is fixedly connected to the telescopic guide connecting piece 25, and the stability of the transmission of the gear 23 and the rack 22 is ensured by the telescopic guide connecting piece 25. Optionally, the telescopic guide connecting piece 25 adopts a frame structure to reduce the weight of the wings 3.

[0045] Optionally, a set of ailerons are arranged at the end of the wings for roll channel control. Specifically, the ailerons are located at the end of the wings away from the body when the wings are unfolded.

[0046] Preferred, such as Figure 2 As shown, the axial section of the missile body 2 corresponding to the wing installation position can be designed as an inclined surface 8 that slopes downwards from the front end to the rear end of the missile body 2. Specifically, the inclined surface 8 is designed in the wing section 13 of the missile body. The inclined surface 8 is provided with a mounting groove 7, which is arranged close to the integrated section 12 of the missile body. The wing deployment mechanism 6 is installed in the mounting groove 7. Through this structural design of the missile body 2, space can be provided for the folded wings 3, reducing the volume of the loitering munition when it is loaded into the launch tube 1.

[0047] Optional implementation methods, such as Figure 11 and Figure 13 As shown, the rudder wing deployment mechanism 9 includes a rudder wing motor 27, a gear transmission assembly, a rudder wing main shaft 34, a rudder wing deployment shaft 33, and a rudder wing torsion spring 35. One end of the rudder wing deployment shaft 33 is fixedly connected to the rudder wing 4, and the other end is connected to the rudder wing main shaft 34 through the rudder wing torsion spring 35. The rudder wing motor 27 is connected to the rudder wing main shaft 34 through the gear transmission assembly to drive the rudder wing main shaft 34 to rotate around its own axis. When the loitering munition is loaded into the launch tube 1, the rudder 4 folds towards the front end of the munition body 2 to the side of the munition body 2. At this time, the rudder torsion spring 35 generates torque, and the launch tube 1 constrains the rudder 4. When the loitering munition is ejected from the launch tube 1, the constraint of the launch tube 1 on the rudder 4 is removed, and the torque of the rudder torsion spring 35 pulls the rudder deployment shaft 33 back to the initial state. The rudder deployment shaft 33 deflects 90°, realizing the deployment of the rudder 4. After the two rudder wings 4 are deployed, they form an inverted V-shaped structure. After the rudder wings 4 are deployed, the rudder motor 27 drives the gear transmission assembly to rotate, which drives the rudder main shaft 34 to rotate, and then drives the rudder deployment shaft 33 to deflect around its axis, realizing the rudder deflection of the rudder 4.

[0048] Specifically, the gear transmission assembly includes a rudder bevel gear 28, a rudder bevel gear 29, a rudder bevel gear shaft 30, a rudder half gear 31, and a rudder half gear 32. The rudder bevel gear 28 is connected to the movable end of the rudder motor 27, the rudder half gear 32 is connected to the rudder main shaft 34, the rudder bevel gear 29 and the rudder half gear 31 are coaxially connected to the rudder bevel gear shaft 30, and the rudder bevel gear 29 and the rudder half gear 31 are respectively meshed with the rudder bevel gear 28 and the rudder half gear 32.

[0049] The wing and the rudder wing of the variable aerodynamic shape cruise missile provided by the utility model are both in a foldable form, are conveniently folded and placed in a launching cylinder before launching, the wing is designed in a telescopic structure form, can be telescoped into different lengths according to flight environment and combat task requirements, the wing aspect ratio is adjusted, the aerodynamic shape of the cruise missile is changed, the cruise time is long, the combat distance is far, the speed range is wide, and the cruise height is high.

[0050] The above examples are only illustrative of the utility model, and do not constitute a limitation on the protection scope of the utility model, and any design identical or similar to the utility model belongs to the protection scope of the utility model.

Claims

1. A variable aerodynamic configuration cruise missile comprising a missile body, two wings and two tail wings, characterized in that: The wings are connected to the front of the body by wing unfolding mechanisms, so that the wings can be folded longitudinally rearward to the body, the wings include outer wings and inner wings, the outer wings and inner wings are connected by wing telescopic mechanisms, the rudders are connected to the rear of the body by rudder unfolding mechanisms, so that the rudders can be folded longitudinally forward to the body.

2. The variable geometry cruise missile of claim 1, wherein: The angle between the two wings is 0 degrees when the wings are folded, and the angle between the two wings is 180 degrees when the wings are unfolded; the two rudders are unfolded in inverted V shape.

3. The variable geometry cruise missile of claim 1, wherein: The wing unfolding mechanism includes a fixed shaft, two tension springs and two connecting cranks, the fixed shaft is fixedly connected to the body, one end of each of the two connecting cranks is connected to one end of each of the two wings, the other end of each of the two connecting cranks is rotatably connected to the fixed shaft, one end of each of the two tension springs is connected to each of the two connecting cranks, and the other end of each of the two tension springs is connected to the body.

4. The variable geometry cruise missile of claim 1, wherein: The axial section of the body corresponding to the wing mounting position has an inclined surface inclined downward from the front end to the rear end of the body, the inclined surface is provided with a mounting groove, and the wing unfolding mechanism is mounted in the mounting groove.

5. The variable geometry cruise missile of claim 1, wherein: The wing telescopic mechanism includes a wing telescopic motor, a gear and a rack, the gear is connected to one end of the inner wing away from the body, the rotation axis of the gear is perpendicular to the length direction of the inner wing, the gear is electrically connected to the wing telescopic motor, the rack is mounted on the inner side wall of the outer wing along the length direction of the outer wing, and the rack is meshingly connected with the gear.

6. The variable geometry cruise missile of claim 5, wherein: The wing telescopic mechanism further includes a telescopic guide connecting piece, the telescopic guide connecting piece is slidably connected between the outer wing and the inner wing, and the rotation axis of the gear is fixedly connected with the telescopic guide connecting piece.

7. The variable geometry cruise missile of claim 1, wherein: The rudder unfolding mechanism includes a rudder motor, a gear transmission assembly, a rudder main shaft, a rudder unfolding shaft and a rudder torsional spring, one end of the rudder unfolding shaft is fixedly connected with the rudder, the other end of the rudder unfolding shaft is connected with the rudder main shaft through the rudder torsional spring, the rudder motor is connected with the rudder main shaft through the gear transmission assembly, so as to drive the rudder main shaft to rotate around its own axis.

8. The variable geometry cruise missile of claim 7, wherein: The gear transmission assembly includes a rudder bevel gear one, a rudder bevel gear two, a rudder bevel gear shaft, a rudder half gear one and a rudder half gear two, the rudder bevel gear one is connected to the movable end of the rudder motor, the rudder half gear two is connected to the rudder main shaft, the rudder bevel gear two and the rudder half gear one are coaxially connected to the rudder bevel gear shaft, and the rudder bevel gear two and the rudder half gear one are meshingly connected with the rudder bevel gear one and the rudder half gear two respectively.

9. The variable geometry cruise missile of claim 1, wherein: The end of the wing away from the body is provided with ailerons for controlling the roll channel when the wing is unfolded.

10. The variable geometry cruise missile of claim 1, wherein: The body includes a warhead, a body and a tail, the warhead is a suspended cabin type seeker, the body is a non-circular cross section, and the tail is contracted from front to back to be a stern shape.

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