Four-rotor missile wing patrol missile

Abstract

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

Description

Technical Field

[0001] This invention relates to the field of loitering munitions, specifically to a quadcopter loitering munition. Background Technology

[0002] Traditional loitering munitions have various wing structures. Some loitering munitions use fixed wings. Although this design is simple, it takes up a lot of space during transportation and storage, which is not conducive to large-scale deployment and covert carrying. Other loitering munitions use folding wings, which are folded and unfolded manually or by simple mechanical devices. However, the unfolding process is relatively cumbersome, and the reliability of the unfolding mechanism needs to be improved. In complex environments, the wings may fail to unfold properly, affecting the normal use of the loitering munition.

[0003] In terms of propulsion systems, traditional loitering munitions mostly use a single propeller or jet engine as their power source. A single propeller propulsion system is insufficient in terms of flight stability and maneuverability, making it difficult to achieve complex maneuvers such as hovering and precise turning; while jet engines are powerful, they consume a lot of energy and are noisy, which is not conducive to long-term loitering and stealth operations.

[0004] As modern military missions place increasingly higher demands on loitering munitions, they require smaller size, more convenient operation, more stable flight performance, and stronger mission adaptability. Therefore, developing a new type of loitering munition with a novel structure and power system has become an urgent problem to be solved. This quadrotor missile-wing loitering munition was developed in response to this background. Summary of the Invention

[0005] To solve the above-mentioned technical problems, the present invention provides the following technical solution: a quadcopter loitering munition, comprising a head, a middle section, and a tail section arranged from front to back. A return spring is built into the middle section along its length. One end of the return spring is connected to the inner wall of the middle section near the head, and the other end is rotatably connected to a front locking assembly. The other end of the front locking assembly is connected to a wing assembly. An ejection channel for the wing assembly is provided on the middle section. The wing assembly is also rotatably connected to the end of the ejection channel away from the head of the loitering munition via a rear locking assembly. When the rear and front locking assemblies rotate to a position parallel to the middle section of the loitering munition, they are retracted into the ejection channel, and the return spring is in a stretched, energy-storing state. Braking and locking mechanisms connected to the return spring and the ejection channel are respectively provided on the rear and front locking assemblies.

[0006] Furthermore, the front locking assembly includes a spring sleeve that is sleeved with a return spring, and a first connecting rod is provided on the spring sleeve, the top of the first connecting rod being rotatably connected to the wing assembly.

[0007] Furthermore, the wing assembly includes a motor rotatably connected to the first link, and a propeller is rotatably connected to the output shaft of the motor, with the propeller facing the tail of the loitering munition.

[0008] Furthermore, the rear locking assembly includes a second link, the top of which is fixedly connected to a motor, and the bottom of which is rotatably connected to the end wall of the ejection channel via the motor.

[0009] Furthermore, the number of the front locking assembly, the rear locking assembly, and the wing assembly is multiple sets, which are circumferentially spaced on the outer wall of the middle part of the loitering munition.

[0010] The advantages of this invention compared to the prior art are:

[0011] This invention achieves rapid switching between the retracted and deployed states of the wing assembly through the design of a return spring and a braking locking mechanism. Before launch, the wing assembly is retracted, reducing the overall volume of the loitering munition and facilitating transportation, storage, and launch. After launch, the wings can be rapidly deployed, quickly entering loitering mode, improving the munition's operational flexibility and response speed. The connection design between the front and rear locking components and the wing assembly is reasonable, with each component cooperating closely. While ensuring the normal deployment and operation of the wing assembly, it effectively utilizes the central space of the loitering munition, resulting in a compact overall structure. Simultaneously, the return spring and braking locking mechanism enhance the structural reliability and reduce the probability of unexpected wing assembly failures. It exhibits strong mission adaptability, allowing for flexible adjustment of motor speed and propeller operating status according to different mission requirements, thereby altering the munition's flight speed, altitude, and attitude. This not only enables it to perform traditional loitering munition tasks and functions but also significantly improves its maneuverability and survivability. Attached Figure Description

[0012] Figure 1 This is a schematic diagram of the front structure of a quadrotor loitering munition according to the present invention.

[0013] Figure 2 This is a schematic diagram of the rear structure of a quadrotor loitering munition according to the present invention.

[0014] Figure 3 This is a schematic diagram of the structure of the wing assembly in a quadrotor loitering munition according to the present invention.

[0015] Figure 4 This is a schematic diagram of the structure of a single wing assembly in a quadrotor loitering munition according to the present invention. Detailed Implementation

[0016] To make the objectives, technical solutions, and advantages of the embodiments of the present invention clearer, the technical solutions of the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only some embodiments of the present invention, and not all embodiments. The components of the embodiments of the present invention described and shown in the accompanying drawings can generally be arranged and designed in various different configurations.

[0017] In the description of the embodiments of the present invention, it should be noted that if terms such as "center," "upper," "lower," "left," "right," "vertical," "horizontal," "inner," and "outer" indicate the orientation or positional relationship based on the orientation or positional relationship shown in the accompanying drawings, or the orientation or positional relationship commonly used when the product of the invention is in use, they are only for the convenience of describing the present invention 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, and therefore should not be construed as a limitation of the present invention. Furthermore, terms such as "first," "second," and "third" are only used to distinguish descriptions and should not be construed as indicating or implying relative importance.

[0018] Furthermore, the use of terms such as "horizontal," "vertical," and "sag" does not imply that the component must be absolutely horizontal or suspended, but rather that it can be slightly tilted. For example, "horizontal" simply means that its direction is more horizontal relative to "vertical," and does not mean that the structure must be completely horizontal, but can be slightly tilted.

[0019] In the description of the embodiments of the present invention, "multiple" means at least two.

[0020] In the description of the embodiments of the present invention, it should also be noted that, unless otherwise explicitly specified and limited, the terms "set," "install," "connect," and "link" should be interpreted broadly. For example, they can refer to a fixed connection, a detachable connection, or an integral connection; they can refer to a mechanical connection or an electrical connection; they can refer to a direct connection or an indirect connection through an intermediate medium; and they can refer to the internal connection of two components. Those skilled in the art can understand the specific meaning of the above terms in the present invention according to the specific circumstances.

[0021] Example:

[0022] A quadcopter loitering munition includes a head 1, a middle section 2, and a tail section 3 arranged from front to rear. A return spring 4 is internally located in the middle section 2 along its length. One end of the return spring 4 is connected to the inner wall of the middle section 2 near the head 1, and the other end is rotatably connected to a front locking assembly 5. The other end of the front locking assembly 5 is connected to a wing assembly 6. An ejection channel 201 for ejecting the wing assembly 6 is provided on the middle section 2. The wing assembly 6 is also rotatably connected to the end of the ejection channel 201 away from the head 1 of the loitering munition via the rear locking assembly 7; when the rear locking assembly 7 and the front locking assembly 5 are rotated to a position parallel to the middle part 2 of the loitering munition, the rear locking assembly 7 and the front locking assembly 5 are housed in the ejection channel 201, and at this time the return spring 4 is in a stretched energy storage state. The rear locking assembly 7 and the front locking assembly 5 are respectively provided with a braking locking mechanism connected to the return spring 4 and the ejection channel 201.

[0023] The front locking assembly 5 includes a spring sleeve 501 that is sleeved with a return spring 4. A first connecting rod 502 is provided on the spring sleeve 501. The top of the first connecting rod 502 is rotatably connected to the wing assembly 6. The wing assembly 6 includes a motor 601 that is rotatably connected to the first connecting rod 502. A propeller 602 is rotatably connected to the output shaft of the motor 601. The propeller 602 is positioned facing the tail 3 of the loitering munition. The rear locking assembly 7 includes a second connecting rod 701. The top of the second connecting rod 701 is fixedly connected to the motor 601, and the bottom is rotatably connected to the end wall of the ejection channel 201 via a rotating shaft 702. There are multiple sets of the front locking assembly 5, the rear locking assembly 7, and the wing assembly 6, which are circumferentially spaced on the outer wall of the middle part 2 of the loitering munition.

[0024] Before launch, the rear locking assembly 7 and the front locking assembly 5 of the quadcopter loitering munition are rotated to a position parallel to the middle part 2 of the loitering munition and stored in the ejection channel 201. At this time, the return spring 4 is in a stretched and energy-storing state, and the braking locking mechanism stably locks the rear locking assembly 7 and the front locking assembly 5 in the stored position, ensuring that the wing assembly 6 will not be accidentally ejected during the transportation, storage and launch preparation stages of the loitering munition, thus ensuring safety.

[0025] When the loitering munition is launched and reaches the predetermined stage, the braking locking mechanism unlocks. Under the action of the return spring 4 releasing elastic potential energy, the front locking assembly 5 and the rear locking assembly 7 drive the wing assembly 6 to rotate around the connection point with the middle part 2 of the loitering munition. The wing assembly 6 pops out and unfolds to 90° along the ejection channel 201. The motor 601 in the wing assembly 6 is powered on and starts. The output shaft of the motor 601 drives the propeller 602 to rotate. Since the propeller 602 is set facing the tail 3 of the loitering munition, the rotating propeller 602 generates forward thrust, providing power for the loitering munition and enabling it to enter loitering mode. By adjusting the speed of each motor 601 through the flight control, roll, pitch and yaw moments are generated, realizing the longitudinal, lateral and directional control of the loitering munition, enabling the loitering munition to complete maneuvering.

[0026] All standard parts used in this invention can be purchased from the market, and irregular parts can be customized according to the description and drawings. The specific connection methods of each part adopt conventional methods such as bolts, rivets, and welding that are mature in the prior art. The machinery, parts and equipment adopt conventional models in the prior art, and the circuit connection adopts conventional connection methods in the prior art, which will not be described in detail here. The contents not described in detail in this specification belong to the prior art known to those skilled in the art.

[0027] The present invention and its embodiments have been described above. This description is not restrictive, and the accompanying drawings are only one embodiment of the present invention; the actual structure is not limited thereto. In conclusion, if those skilled in the art are inspired by this description and design similar structures and embodiments without departing from the spirit of the invention, such designs should fall within the protection scope of the present invention.

Claims

1. A quadcopter-winged loitering munition, characterized in that, The loitering munition comprises a head, a middle section, and a tail section arranged from front to back. A return spring is built into the middle section along its length. One end of the return spring is connected to the inner wall of the middle section near the head, and the other end is rotatably connected to a front locking assembly. The other end of the front locking assembly is connected to a wing assembly. An ejection channel for the wing assembly is provided on the middle section. The wing assembly is also rotatably connected to the end of the ejection channel away from the head via a rear locking assembly. When the rear and front locking assemblies rotate to a position parallel to the middle section, they are retracted into the ejection channel, and the return spring is in a stretched, energy-storing state. Braking and locking mechanisms connected to the return spring and ejection channel are respectively provided on the rear and front locking assemblies.

2. The quadrotor-wing loitering munition according to claim 1, characterized in that, The front locking assembly includes a spring sleeve that is sleeved with a reset spring, and a first connecting rod is provided on the spring sleeve. The top of the first connecting rod is rotatably connected to the wing assembly.

3. A quadcopter-winged loitering munition according to claim 1, characterized in that, The missile wing assembly includes a motor rotatably connected to the first link, and a propeller rotatably connected to the output shaft of the motor, with the propeller facing the tail of the loitering missile.

4. A quadcopter-winged loitering munition according to claim 1, characterized in that, The rear locking assembly includes a second link, the top of which is fixedly connected to a motor, and the bottom of which is rotatably connected to the end wall of the ejection channel via the motor.

5. A quadcopter-winged loitering munition according to claim 1, characterized in that, The number of the front locking assembly, rear locking assembly, and wing assembly is multiple, and they are circumferentially spaced on the outer wall of the middle part of the loitering munition.

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