Variable-wing patrolling bomb structure

Abstract

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

Description

Technical Field

[0001] This utility model belongs to the field of variable-wing loitering munitions, and particularly relates to a variable-wing loitering munition structure. Background Technology

[0002] The integrated reconnaissance and strike warfare model, characterized by clustered operations, air-ground coordination, and stand-off strike capabilities, places increasingly higher demands on the loiter time and multi-platform launch capabilities of low-cost munitions. Currently deployed and under-development loitering munitions are primarily low-speed, while high-subsonic loitering munitions are limited by lift constraints, resulting in a narrow speed range. This aerodynamic configuration of loitering munitions leads to the following shortcomings in their use.

[0003] 1. Single launch platform

[0004] Current loitering munitions are primarily ground-launched, with flight speeds between 90 km / h and 150 km / h. To improve lift at low speeds, these munitions typically employ aerodynamic configurations with straight, unswept wings. However, straight-wing loitering munitions are ill-suited for high subsonic flight, while fighter jets generally operate at high subsonic speeds. Ground-launched loitering munitions are therefore ill-suited for fighter jet launches. This type of loitering munition, designed only for ground launches and incompatible with fighter jet launches, fails to meet the requirements for weapon versatility.

[0005] 2. Poor ability to strike time-sensitive targets promptly.

[0006] For low-speed loitering munitions, the relatively long flight time from launch to the target area, coupled with the real-time changes in the target, increases the difficulty of target search, identification, tracking, and engagement. This necessitates rapid flight from the launch point to the sensitive area, and, once there, the ability to accurately search for targets in complex terrain conditions.

[0007] In general, current loitering munitions only have the ability to open their wings once, which cannot meet the requirements for use in multiple scenarios. Utility Model Content

[0008] The purpose of this invention is to provide a variable-wing loitering munition structure to meet the needs of launching from multiple platforms, including ground, fighter jets, drones, and helicopters.

[0009] To address the above problems, this utility model discloses a variable-wing loitering munition structure, including a munition body, a warhead, and a tail. The munition body is equipped with folding wings, a front locking mechanism, and a rear locking mechanism. The front locking mechanism is connected to one end of the folding wings, and the rear locking mechanism is connected to the other end of the folding wings. A front elastic deployment mechanism is provided between the folding wings and the munition body. The folding wings include a first deployment arm and a second deployment arm, which are hinged together. A rear elastic deployment mechanism is provided between the first and second deployment arms. The first deployment arm is connected to the front locking mechanism, and the second deployment arm is connected to the rear locking mechanism. A slide rail is provided on the munition body, and a slider is slidably mounted on the slide rail. The rear locking mechanism is mounted on the slider.

[0010] Preferably, the folding wings are symmetrically arranged on the projectile body.

[0011] Preferably, the rear of the projectile is provided with a sinking area to accommodate a folding wing, and the height of the folding wing after installation is lower than the height of the front of the projectile.

[0012] Preferably, the missile tail is provided with a tail fin. The tail fin can be a fixed fin or a folding fin structure, which can be designed according to requirements.

[0013] Preferably, a propeller is provided on the tail of the projectile. This propeller is driven by an electric motor and can participate in the control of speed and direction.

[0014] Preferably, both the front elastic deployment mechanism and the rear elastic deployment mechanism include a wing seat and a leaf spring; one end of the leaf spring is inserted into the wing seat, and the other end abuts against the folding wing.

[0015] Preferably, the front locking mechanism includes a compression spring and a front locking pin, and a first pin hole is provided at the front end of the first unfolding arm, with the front locking pin engaging with the first pin hole.

[0016] Preferably, the rear locking mechanism includes an extendable arm electromagnet mounted on the slider, and a second pin hole is provided on the second extendable arm, with the output end of the extendable arm electromagnet cooperating with the second pin hole.

[0017] Compared with the prior art, the beneficial effects of this utility model are:

[0018] High flexibility: By setting up a flexible deployment mechanism and front and rear locking mechanisms, the folding wing can be deployed according to different flight requirements and adapt to different flight speeds and conditions.

[0019] High adaptability: The folding wings can automatically adjust the wing deployment mode according to the speed of the launch platform and environmental conditions, realizing the switching from high-speed to low-speed flight and improving the battlefield adaptability of the loitering munition.

[0020] High concealment: Before launch, the folding wings and propellers are folded, reducing the size of the loitering munition and making it easier to carry and launch covertly.

[0021] High flight efficiency: During high-speed flight, the folding wings have a certain sweep angle, which reduces flight drag; during low-speed flight, the folding wings are extended to their limit position, reducing the sweep angle, which is suitable for low-speed gliding.

[0022] Easy to control: The front and rear locking mechanisms are operated through the control module to realize the unfolding and locking of the folding wings. The operation is simple and highly reliable.

[0023] Compact structure: It adopts leaf springs and wing mounts as elastic deployment mechanism, which is compact, occupies little space, and helps to reduce the overall weight of the loitering munition.

[0024] Wide range of applications: The variable-wing loitering munition structure of this embodiment can be applied to various occasions such as ground launch, low-speed UAV platform deployment and high-speed platform launch, and has a wide range of application prospects.

[0025] Safe and reliable: By measuring flight speed and altitude in real time, the flight control system on the loitering munition can accurately control the timing of the folding fins' deployment, ensuring that the loitering munition flies stably at the predetermined altitude and speed. Attached Figure Description

[0026] Figure 1 This is a schematic diagram of the loitering munition of this utility model before it is deployed;

[0027] Figure 2 This is a schematic diagram of the high-speed flight structure of the loitering munition of this utility model;

[0028] Figure 3 This is a schematic diagram of the low-speed flight structure of the loitering munition of this utility model;

[0029] Figure 4 This is a side view of the loitering munition of this utility model before it is deployed.

[0030] Figure 5 This is a schematic diagram of the folding wing structure of this utility model;

[0031] Figure 6 This is a schematic diagram of the installation structure of the front elastic deployment mechanism of this utility model;

[0032] Figure 7 This is a schematic diagram of the installation structure of the rear elastic deployment mechanism of this utility model;

[0033] Figure 8 This is a schematic diagram of the rear locking mechanism of this utility model;

[0034] Figure 9 This is a schematic diagram of the first deployable arm structure of this utility model;

[0035] Figure 10 This is a schematic diagram of the second deployable arm structure of this utility model.

[0036] Reference numerals: 1. Projectile body; 10. Slide rail; 100. Sinking area; 11. Front locking mechanism; 112. Wing seat; 113. Leaf spring; 114. Compression spring; 115. Front locking pin; 12. Rear locking mechanism; 13. Front elastic deployment mechanism; 14. Rear elastic deployment mechanism; 15. Extending arm electromagnet; 16. Slider; 2. Projectile head; 3. Projectile tail; 31. Tail fin; 32. Propeller; 4. Folding wing; 41. First deploying arm; 411. First pin hole; 42. Second deploying arm; 421. Second pin hole. Detailed Implementation

[0037] To make the technical means, creative features, objectives and effects of this utility model easier to understand, the present utility model will be further described below in conjunction with specific embodiments.

[0038] In the description of this utility model, it should be noted that the terms "upper," "lower," "inner," "outer," "front end," "rear end," "both ends," "one end," and "the other end," etc., indicate the orientation or positional relationship based on the orientation or positional relationship shown in the accompanying drawings. They are used only for the convenience of describing this utility model and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, or be constructed and operated in a specific orientation. Therefore, they should not be construed as limitations on this utility model. In addition, the terms "first" and "second" are used for descriptive purposes only and should not be construed as indicating or implying relative importance.

[0039] In the description of this utility model, it should be noted that, unless otherwise explicitly specified and limited, the terms "installed," "equipped with," and "connected," etc., should be interpreted broadly. For example, "connected" can be a fixed connection, a detachable connection, or an integral connection; it can be a mechanical connection or an electrical connection; it can be a direct connection or an indirect connection through an intermediate medium; it can be a connection within two components. Those skilled in the art can understand the specific meaning of the above terms in this utility model based on the specific circumstances.

[0040] The technical solutions of the present utility model will be clearly and completely described below with reference to the accompanying drawings of the embodiments. Obviously, the described embodiments are only some embodiments of the present utility model, and not all embodiments. Based on the embodiments of the present utility model, all other embodiments obtained by those of ordinary skill in the art without creative effort are within the protection scope of the present utility model.

[0041] like Figures 1 to 10As shown, the variable-wing loitering munition structure of this embodiment includes a munition body 1, a warhead 2 and a tail 3. The munition body 1 is provided with a folding wing 4. The munition body 1 is provided with a front locking mechanism 11 and a rear locking mechanism 12. The front locking mechanism 11 is connected to one end of the folding wing 4, and the rear locking mechanism 12 is connected to the other end of the folding wing 4. A front elastic deployment mechanism 13 is provided between the folding wing 4 and the munition body 1.

[0042] The folding wing 4 includes a first deployable arm 41 and a second deployable arm 42, which are hinged together. A rear elastic deployment mechanism 14 is provided between the first deployable arm 41 and the second deployable arm 42. The first deployable arm 41 is connected to the front locking mechanism 11, and the second deployable arm 42 is connected to the rear locking mechanism 12.

[0043] The projectile 1 is provided with a slide rail 10, and a slider 16 is slidably mounted on the slide rail 10. The rear locking mechanism 12 is installed on the slider 16.

[0044] Both the front elastic deployment mechanism 13 and the rear elastic deployment mechanism 14 include a wing seat 112 and a leaf spring 113. One end of the leaf spring 113 is inserted into the wing seat 112, and the other end abuts against the folding wing 4. The front wing seat 112 is mounted on the front mounting bracket and fixed by the first locking screw 116. One end of the front leaf spring 113 abuts against the first deployment arm 41, and the other end is inserted into the front wing seat 112. After the external force is removed, the first deployment arm 41 is deployed under the action of the front leaf spring 113. The shaft end of the wing seat 112 is provided with a through groove that mates with the inner ring of the leaf spring 113. The large end flange of the wing seat 112 is provided with four notches along the circumferential direction that mate with the first locking screw 116. The leaf spring 113 is installed at the connection point at the root of the first deployment arm 41. Rotate the wing seat 112 along the unfolding direction until a certain angle is reached, then install the first locking screw 116 through the notch of the wing seat 112, so that the leaf spring 113 stores a certain spring force, and the outer ring of the leaf spring 113 acts on the root of the first unfolding arm 41.

[0045] The rear wing seat 112 is installed at the tail of the first deployable arm 41 and fixed by the second locking screw 117. The tail of the first deployable arm 41 has a receiving cavity. The front part of the second deployable arm 42 is hinged and installed in the receiving cavity. The rear leaf spring 113 moves and is inserted into the rear wing seat 112, and the other end abuts against the second deployable arm 42. After the external force is removed, the second deployable arm 42 unfolds under the action of the rear leaf spring 113. The rear wing seat 112 has a through groove at its shaft end that mates with the inner ring of the leaf spring 113. The large end flange side of the rear wing seat 112 has a semicircle that mates with a pin. The rear leaf spring 113 is located in the inner groove at the root of the second deployable arm 42. The root of the second deployable arm 42, along with the rear leaf spring 113, is placed in the inner groove of the outer connector of the first deployable arm 41. The wing seat 112 passes through the shaft hole at the end of the outer connector of the first deployable arm 41, the shaft hole at the end of the second deployable arm 42, and the inner ring of the leaf spring 113, forming a hinge structure between the outer connector of the first deployable arm 41 and the second deployable arm 42. The outer ring of the leaf spring 113 acts on the side wall of the inner groove at the root of the second deployable arm 42, pushing the second deployable arm 42 outward during deployment. The semicircle at the end of the rotating wing seat 112 coincides with the semicircle at the shaft hole of the outer connector of the first deployable arm 41, and the second locking screw 117 is inserted into the semicircular hole to form a tight fit. The leaf spring of the unfolding mechanism possesses elastic potential energy to drive the unfolding of the second unfolding arm 42. In the retracted state, the leaf spring stores elastic potential energy. When unfolding, the leaf spring quickly drives the unfolding arm to unfold. When fully unfolded, some elastic potential energy in the leaf spring is not fully released, thus eliminating the need to lock the second unfolding arm 42. To improve strength, a locking pin, similar to the previous locking mechanism, can be installed here. When the second unfolding arm 42 is fully unfolded, the locking pin extends under the action of the compression spring and inserts into the second unfolding arm 42 for limiting its position.

[0046] The front locking mechanism 11 includes a compression spring 114 and a front locking pin 115. The front end of the first unfolding arm 41 is provided with a first pin hole 411, and the front locking pin 115 engages with the first pin hole 411. When the first unfolding arm 41 is fully unfolded, the first pin hole 411 is aligned with the front locking pin 115, and the front locking pin 115 is pushed up under the action of the compression spring 114, so that the front locking pin 115 extends into the first pin hole 411, thereby limiting the first unfolding arm 41.

[0047] The rear locking mechanism 12 includes an extension arm electromagnet 15 mounted on the slider 16. A second pin hole 421 is provided on the second extension arm 42, and the output end of the extension arm electromagnet 15 cooperates with the second pin hole 421. The first working state of the extension arm electromagnet 15 is extended, and the second working state is retracted. In the first working state, the tail of the second extension arm 42 is limited and cannot be fully extended. In the second working state, the second extension arm 42 is unrestricted and fully extended under the action of the rear leaf spring 113.

[0048] The slider 16 is provided with a third pin hole 161, and the slide rail 10 is provided with a limiting electromagnet 17. The output end of the limiting electromagnet 17 cooperates with the third pin hole 161. The first unfolding arm 41 requires the cooperation of the second unfolding arm 42 to unfold. If the second unfolding arm 42 does not rotate, the first unfolding arm 41 cannot unfold. The limiting electromagnet 17 is used to unlock the second unfolding arm 42 (in other words, it is also used to unlock the first unfolding arm 41). The limiting electromagnet 17 also has a first working state (extended) and a second working state (retracted). In the first working state, the limiting electromagnet 17 is inserted into the third pin hole 161 and is limited. After the external force (from the launching platform) is removed, neither the first unfolding arm 41 nor the second unfolding arm 42 can unfold. In the second working state, the first unfolding arm 41 unfolds, and at the same time, one end of the second unfolding arm 42 moves with the slider 16 and partially unfolds, resulting in... Figure 2 As shown in the diagram. When the extension arm electromagnet 15 of the rear locking mechanism 12 is in the second working state, the second extension arm 42 is completely released from its restraint, and the first extension arm 41 is no longer restrained by the second extension arm. Both are fully extended under the action of the leaf spring 113. The front locking pin 115 of the front locking mechanism 11 of the first extension arm 41 extends under the action of the compression spring 114, completing the limitation of the first extension arm 41, thus achieving... Figure 3 The state shown.

[0049] The folding wings 4 are symmetrically arranged on the missile body 1. The symmetrical distribution is conducive to stable flight.

[0050] The rear of the projectile 1 has a recessed area 100 to accommodate the folding wing 4. After installation, the height of the folding wing 4 is lower than the height of the front of the projectile 1. This design helps to reduce wind resistance when the wing is not deployed.

[0051] The tail fin 31 is mounted on the tail of the missile. A propeller 32 is also mounted on the tail fin 3. The tail fin and propeller are used to coordinate and control the flight direction. A control unit is located within the missile body 1 or the warhead 2. This control unit includes an altimeter, speedometer, gyroscope (INS300 series integrated inertial navigation system), and control module. The control module controls the opening and closing of the electromagnets and the rotational speed of the propeller 32. The propeller 32 can be a folding propeller (selected according to the launch bay; if there are no restrictions, a fixed fin can be used; the folding propeller unfolds under the centrifugal force of the propeller rotation), and automatically unfolds when there is no external force restriction. The control module can automatically control the opening and closing of the electromagnets based on real-time altitude and speed information (altitude and speed parameters are preset values), or it can use remote control to open and close the electromagnets. According to the loitering munition design, the warhead 2 should be equipped with a camera and other mechanisms for information collection (reconnaissance). Since this application only protects the structure, the details are not elaborated here.

[0052] like Figure 1The diagram shown is a schematic of the loitering munition of this utility model before it is deployed. It should be noted that the propeller 32 is also a foldable structure; that is, the fins are folded before launch. When the loitering munition is deployed as shown... Figure 1 After the structure shown takes off, propeller 32 deploys. Then, the control module controls the limiting electromagnet 17 of the rear locking mechanism 12 to unlock, and the first deploying arm 41 and the second deploying arm 42 deploy under the action of leaf spring 113. Sliding slider 16 slides on slide rail 10 until it reaches the stop position on slide rail 10, achieving a certain sweep angle. Figure 2 The state shown is suitable for high-speed flight. When low-speed flight is required, the sweep angle is changed to achieve low-speed flight. Specifically, the two extendable arm electromagnets 15 of the rear locking mechanism 12 start to operate, releasing the restriction on the second extendable arm 42. Under the action of the leaf spring 113, the first extendable arm 41 and the second extendable arm 42 extend to their limit positions, so that the sweep angle reaches the minimum. When the first extendable arm 41 reaches its limit position, the front locking pin 115 pops out under the action of the internal compression spring 114, locking the first extendable arm 41. This state is suitable for low-speed flight.

[0053] The folding wing 4 adopts different wing deployment methods according to the wing deployment command. For example, when launched from the ground or deployed from a low-speed unmanned aerial vehicle platform, the wings deploy as follows: Figure 3 The structure shown. If launched from a high-speed platform, the wings first deploy as shown... Figure 2 As shown. After launch from the high-speed platform, the loitering munition... Figure 2 The loitering munition is gliding in the indicated state. The flight control system on the munition measures its speed in real time. When the speed decreases to a certain level, the flight control system issues another wing-spreading command, and the munition unfolds as shown. Figure 3 Flight as shown.

[0054] The variable-wing loitering munition structure of this invention exhibits excellent lift characteristics at different speeds, solving the aerodynamic design challenges of loitering munitions at different speeds; it also has the advantages of simple structure, low cost, and high reliability.

[0055] The above description is merely an embodiment of this utility model, and common knowledge regarding specific structures and characteristics is not described in detail here. It will be apparent to those skilled in the art that this utility model is not limited to the details of the above exemplary embodiments, and that it can be implemented in other specific forms without departing from the spirit or essential characteristics of this utility model. Therefore, the embodiments should be considered exemplary and non-limiting in all respects, and the scope of this utility model is defined by the appended claims rather than the foregoing description. Thus, it is intended that all variations falling within the meaning and scope of equivalents of the claims be included within this utility model. No reference numerals in the claims should be construed as limiting the scope of the claims.

Claims

1. A variable wing cruise missile structure comprising a missile body (1), a missile head (2) and a missile tail (3), a folding wing (4) being provided on the missile body (1), characterized in that: The projectile (1) is provided with a front locking mechanism (11) and a rear locking mechanism (12). The front locking mechanism (11) is connected to one end of the folding wing (4), and the rear locking mechanism (12) is connected to the other end of the folding wing (4). A front elastic deployment mechanism (13) is provided between the folding wing (4) and the projectile (1). The folding wing (4) includes a first deployable arm (41) and a second deployable arm (42), the first deployable arm (41) and the second deployable arm (42) are hinged together, a rear elastic deployable mechanism (14) is provided between the first deployable arm (41) and the second deployable arm (42), the first deployable arm (41) is connected to the front locking mechanism (11), and the second deployable arm (42) is connected to the rear locking mechanism (12); The projectile (1) is provided with a slide rail (10), and a slider (16) is slidably provided on the slide rail (10). The rear locking mechanism (12) is installed on the slider (16).

2. The variable wing cruise missile structure of claim 1, wherein The folding wings (4) are symmetrically arranged on the projectile body (1).

3. The variable-wing cruise missile structure of claim 2, wherein The projectile (1) has a sinking area (100) at the rear to accommodate the folding wing (4), and the height of the folding wing (4) after installation is lower than the height of the front of the projectile (1).

4. The variable-wing cruise missile structure of claim 1, wherein The tail of the projectile (3) is provided with a tail fin (31).

5. The variable-wing cruise missile structure of claim 1, wherein A propeller (32) is provided on the tail of the projectile (3).

6. The variable-wing cruise missile structure of any one of claims 1 to 5, wherein, The front elastic deployment mechanism (13) and the rear elastic deployment mechanism (14) both include a wing seat (112) and a leaf spring (113); one end of the leaf spring (113) is inserted into the wing seat (112), and the other end abuts against the folding wing (4).

7. The variable-wing cruise missile structure of claim 5, wherein The front locking mechanism (11) includes a compression spring (114) and a front locking pin (115). The front end of the first unfolding arm (41) is provided with a first pin hole (411), and the front locking pin (115) cooperates with the first pin hole (411).

8. The variable-wing cruise missile structure of claim 6, wherein The rear locking mechanism (12) includes an extended arm electromagnet (15) mounted on a slider (16), and a second pin hole (421) is provided on the second extended arm (42). The output end of the extended arm electromagnet (15) cooperates with the second pin hole (421).

9. The variable-wing cruise missile structure of claim 8, wherein The slider (16) is provided with a third pin hole (161), and the slide rail (10) is provided with a limit electromagnet (17). The output end of the limit electromagnet (17) is engaged with the third pin hole (161).

Images