Hidden foldable bee colony unmanned aerial vehicle

Abstract

The invention discloses an invisible foldable swarm unmanned aerial vehicle, which relates to the technical field of unmanned aerial vehicles, and comprises a fuselage, two wings symmetrically arranged on two sides of the upper part of the middle part of the fuselage, two empennages arranged on two sides of the tail part of the fuselage, a thrust propeller arranged on the tail part of the fuselage, and ailerons arranged on the rear sides of the wings; folding mechanisms with elastic memory recovery are arranged at the joints of the wings and the fuselage, the joints of the empennages and the fuselage and the joints of the thrust propellers and the fuselage; the overall cross section of the fuselage is of a big-end-up trapezoidal structure used for reducing the radar reflection coefficient. According to the invisible foldable unmanned aerial vehicle, the wings and the empennage are designed to be folded and unfolded, honeycomb type storage of the unmanned aerial vehicle can be achieved, and rapid maneuvering and dense launching are achieved. The radar discovery rate can be reduced through the accurate appearance design, noise can be reduced through propeller propulsion, the concealment of the unmanned aerial vehicle is higher, and the battlefield survival rate and the saturation strike capacity of the unmanned aerial vehicle can be improved through the bee colony technology.

Description

Technical Field

[0001] This invention relates to the field of unmanned aerial vehicle (UAV) technology, and more specifically to the field of stealthy foldable swarm UAV technology. Background Technology

[0002] With the rapid development of drone technology, drones are increasingly widely used in military, civilian, and commercial fields. The operational needs for drones in warfare are becoming increasingly apparent. One development direction for drones is towards low cost, miniaturization, stealth, collaborative networking intelligent swarms, and large-scale deployment for battlefield reconnaissance and strike operations. Currently, small drones used on the battlefield are easily detected and identified by forward-deployed radar. Due to their weak stealth and penetration capabilities, drones are easily detected and shot down when entering enemy territory. Existing patents disclose the following: Patent CN107685868A, entitled "A High Subsonic Stealth Unmanned Aerial Vehicle," discloses the following: A high subsonic stealth unmanned aerial vehicle (UAV) includes a UAV fuselage, foldable wings and a foldable tail, and a retractable air intake. The UAV fuselage features a stealth design; the wings adopt a high-wing configuration and a rotary folding mechanism, retracting towards the tail; the tail adopts a V-shaped configuration, rotating along the side of the fuselage towards the nose when folded. To accommodate the wing and tail layout and facilitate placement and fixation, the fuselage adopts an integrated design, with its back parallel to the horizontal plane and the side of the fuselage aligned with the dihedral angle of the V-shaped tail. The air intake retracts into the fuselage before the wings are deployed, facilitating transportation and mounting. This invention possesses excellent stealth performance and high subsonic cruise capability, overcoming the shortcomings of small UAVs due to their slow speed and weak penetration ability, while also allowing for the loading of more UAVs within the limited carrying space of the mother aircraft.

[0003] The patent with publication number CN107472509A and patent title "A Flying Wing Stealth Unmanned Aerial Vehicle" discloses the following: A flying wing stealth unmanned aerial vehicle includes a flying wing overall structure, a power system, a flight control system, and a leading edge load mounting system. The flying wing overall structure includes a left wing section and a right wing section. The right wing section includes a right first wing section, a right second wing section, and a right third wing section. The airfoil of the right first wing section is a negative camber airfoil transitioning to an S-shape at the tip. The airfoil is as follows: the root airfoil of the second right wing segment is the same as the tip airfoil of the first right wing segment, and the tip airfoil of the second right wing segment is a high-camber airfoil; the root airfoil of the third right wing segment is the same as the tip airfoil of the second right wing segment, and the tips converge to a single point; the leading edges of the first, second, and third right wing segments are located on the same straight line and have the same leading edge sweep angle; the trailing edges of the first right wing segment, the third right wing segment, and the second left wing segment are arranged parallel to each other. The UAV provided by this invention has the characteristics of high flight performance, high stealth performance, and low manufacturing cost.

[0004] None of the aforementioned patents and existing technologies address stealthy small unmanned aerial vehicles (UAVs) with stealth characteristics and ease of wartime deployment for swarm warfare. Traditional UAV aerodynamic layouts may present problems such as deployment difficulties and easy detection during flight. To solve these problems, it is necessary to research an advanced UAV with stealth characteristics, swarm launch capabilities, and convenient storage and transportation to meet the ever-growing market demand. Summary of the Invention

[0005] The purpose of this invention is to provide a stealthy, foldable swarm drone in order to solve the above-mentioned technical problems.

[0006] To achieve the above objectives, the present invention specifically adopts the following technical solution: The present invention provides a stealthy foldable swarm drone, including a fuselage, two wings symmetrically arranged on both sides of the upper middle part of the fuselage, two tail wings arranged on both sides of the tail of the fuselage, a thrust propeller arranged at the tail of the fuselage, and ailerons arranged on the rear side of each wing. Each wing-fuselage connection, each tail-fuselage connection, and each thrust propeller-fuselage connection is equipped with a folding mechanism with elastic memory recovery. The overall cross-section of the fuselage is a trapezoidal structure with a smaller upper section and a larger lower section, designed to reduce radar reflection coefficient.

[0007] Specifically, the wings, tail, and fuselage are connected by a folding mechanism, which can meet the space requirements of the UAV in different operating states, enabling small-space cellular storage, dense launch, and swarm warfare. The ailerons are connected to the corresponding wings to adjust the UAV's roll attitude.

[0008] In one embodiment, the wing adopts a swept high-wing configuration, and the tail adopts a swept V-shaped configuration; the wing folds backward via the folding mechanism, the tail folds forward, and the thrust propeller folds backward.

[0009] In one implementation, the wing adopts a 30°~34° swept high-wing configuration.

[0010] Specifically, the wings provide the lift required for the UAV's flight. The shape and size of the wings have been precisely optimized to improve the lift coefficient and reduce induced drag. This design incorporates wing stealth technology. The wings are fixed to the fuselage and employ a 30°~34° swept high-wing configuration to reduce radar wave reflection intensity and enhance stealth capabilities. Wingtip shaping and refined airfoil design improve the aircraft's lift-to-drag ratio, while the shape and size of the tail fin have been precisely optimized to reduce radar reflection coefficient.

[0011] In one embodiment, the tail fin adopts a symmetrical V-shaped layout with a 30°~34° sweepback, and the fuselage side forms a 55° angle with the dihedral angle of the V-shaped tail fin.

[0012] Specifically, the tail fin provides stability and maneuverability for the UAV, controlling its pitch and yaw angles. This design details the tail fin's stealth design: the tail fin is fixed to the rear of the fuselage and employs a symmetrical V-shaped layout with a 30°~34° sweepback. The fuselage side and the V-shaped tail fin form a 55° dihedral angle, providing pitch and yaw control. The tail fin maintains the same sweep angle as the wing, regulating the direction of radar wave reflection to a unified direction, reducing the forward radar cross-section. The shape and size of the tail fin have been precisely optimized to reduce the radar reflection coefficient.

[0013] In one implementation, the two wings are symmetrically folded and overlap vertically.

[0014] Specifically, the two wings adopt a symmetrical folding design, overlapping vertically, which can significantly increase the wing area.

[0015] In one embodiment, the nose of the fuselage has a parabolic outer contour, the fuselage body adopts a trapezoidal variable cross-section shape from front to back to reduce the forward radar cross-section, and the rear of the fuselage has a tail cone rectification design to facilitate the loading of airborne equipment and maintain the balance and stability of the UAV.

[0016] Specifically, the streamlined fuselage design reduces aerodynamic drag during drone flight, improving flight efficiency. The fuselage adopts a trapezoidal shape with sloping sides for stealth. The wings and tail employ a regular echo-oriented stealth design, and the angles of the wings and tail are precisely calculated. The dimensions of the thrust propeller are also precisely calculated.

[0017] In one embodiment, the fuselage belly is provided with an irregularly shaped rectifier protrusion, and the irregularly shaped rectifier protrusion is provided with several external interfaces.

[0018] Specifically, the optimized design of the external interface, featuring an irregularly shaped, streamlined protrusion on the fuselage belly, allows for the expansion of external communication interfaces without requiring additional structural components. This design facilitates the expansion of external communication interfaces while maintaining the integrity of the airframe structure. The external interface enhances the versatility of the UAV's mission payload, data communication capabilities, and ease of use.

[0019] The shapes and angles of the fuselage and external interfaces, as well as the wings and tail, have been precisely calculated to enhance stealth capabilities and provide excellent lift-drag and handling characteristics. The propeller dimensions have also been optimized.

[0020] In one embodiment, each folding mechanism includes a support shaft fixed to the fuselage, an elastic memory recovery member fixedly sleeved on the support shaft, a connecting portion disposed on the elastic memory member, and a wing locking pin disposed on the connecting portion. The wings, tail, and thrust propeller are glued or plugged into their respective connecting parts.

[0021] In one embodiment, the elastic memory component includes a fixed sleeve fixedly sleeved on a support shaft, and multiple memory metal springs fixedly connected to the outer wall of the fixed sleeve in a circumferential manner, with the other end of the memory metal springs connected to a connecting part. The fixing sleeve, all memory metal springs, and connecting parts are integrally molded.

[0022] Specifically, the elastic memory component adopts a structural form that combines memory metal and flat spring.

[0023] In one embodiment, the connecting part is provided with a connecting groove that can be inserted or bonded to the root of the wing surface. The wing surface locking pin is provided on the connecting part near the root of the wing surface. The wing surface locking pin includes a spring and a locking pin. The fuselage is provided with locking holes that cooperate with the wing surface locking pin in the unfolded state of the wing, tail, and thrust propeller. The fuselage is also provided with a limiting mechanism for restraining the folded wing, tail, and thrust propeller.

[0024] Specifically, the wing locking pins are arranged on the connecting parts near the wing roots of various wing surfaces to meet the wing locking requirements. The folding drive device differs from traditional folding methods, using shape memory alloy metal as the power source for the torsional drive, resulting in a simple, compact, and highly reliable structure. The folding mechanism utilizes the property of shape memory alloy springs to return to their initial state after deformation to achieve the wing's folding and unfolding function. The wing rotates around the support shaft, and the connecting parts are positioned using keys or pins, while the support shaft remains stationary. The wing locking pins lock the wing's position after unfolding.

[0025] The beneficial effects of this invention are as follows: 1. The stealthy foldable UAV proposed in this invention features foldable and retractable wings and tail fins, enabling honeycomb-like storage and rapid maneuverability with dense launch capability. Precise shape design reduces radar detectability, and propeller propulsion reduces noise, further enhancing the UAV's stealth capabilities. Combined with swarm technology, this improves its battlefield survivability and saturation strike capability.

[0026] 2. The stealthy aerodynamic shape adopted in this invention provides a stealthy foldable UAV with swept-back wings, low radar reflection coefficient, and a simple and compact structure. It is folded during storage, transportation, and launch, and its wings are deployed during flight, propelled by a propeller. This UAV not only possesses good stealth characteristics combined with its foldable function, saving storage space, but also adapts to different launch platforms, enhancing its mobile deployment capabilities, battlefield survivability, and deterrent effect against the enemy.

[0027] The stealth design reduces the forward radar cross-section, enhancing the drone's battlefield survivability.

[0028] 3. The foldable airframe structure allows for switching between a folded state during storage and transportation and an unfolded state after launch, reducing storage space and enabling honeycomb-style loading and transportation. Honeycomb storage provides high mobility and allows for swarm warfare.

[0029] 4. The streamlined fuselage design and smooth surfaces reduce air resistance and energy consumption. The swept-back wing design lowers the radar reflection coefficient, reduces induced drag, and further lowers energy consumption. The swept-back tail design reduces the forward radar cross-section. The combination of the V-shaped tail and all-moving control surfaces reduces structural complexity and enhances the control efficiency of the tail rudder. The integration of ailerons and the tail improves the stability and maneuverability of the UAV. Attached Figure Description

[0030] To more clearly illustrate the technical solutions of the embodiments of the present invention, the accompanying drawings used in the embodiments will be briefly introduced below. It should be understood that the following drawings only show some embodiments of the present invention and should not be regarded as a limitation of the scope. For those skilled in the art, other related drawings can be obtained from these drawings without creative effort.

[0031] Figure 1 This is a top view of the unfolded stealth foldable swarm drone of the present invention.

[0032] Figure 2 yes Figure 1 Rear view.

[0033] Figure 3 yes Figure 1 A bottom view.

[0034] Figure 4 yes Figure 1 The left view.

[0035] Figure 5 yes Figure 1 The left view.

[0036] Figure 6 yes Figure 1 A schematic diagram of the folded structure.

[0037] Figure 7 yes Figure 6 The left view.

[0038] Figure 8 This is a schematic diagram of the folding mechanism.

[0039] Reference numerals: 1. Fuselage; 2. Wing; 3. Tail; 4. Aileron; 5. External interface; 6. Thrust propeller; 7. Wing root; 8. Wing locking pin; 9. Folding mechanism; 10. Support shaft. Detailed Implementation

[0040] To make the technical problems, technical solutions, and technical effects 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.

[0041] Therefore, the following detailed description of the embodiments of the invention provided in the accompanying drawings is not intended to limit the scope of the claimed invention, but merely to illustrate selected embodiments of the invention. All other embodiments obtained by those skilled in the art based on the embodiments of the invention without inventive effort are within the scope of protection of the invention.

[0042] It should be noted that similar reference numerals and letters in the following figures indicate similar items; therefore, once an item is defined in one figure, it does not need to be further defined and explained in subsequent figures. Furthermore, the terms "first," "second," etc., are used only to distinguish descriptions and should not be construed as indicating or implying relative importance.

[0043] In the description of the embodiments of the present invention, it should be noted that the terms "inner", "outer", "upper", etc., indicate the orientation or positional relationship based on the orientation or positional relationship shown in the accompanying drawings, or the orientation or positional relationship in which the product of the invention is usually placed when 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. Therefore, they should not be construed as limiting the present invention.

[0044] Example 1 like Figures 1 to 8 As shown, this embodiment provides a stealthy foldable swarm drone, including a fuselage 1, two wings 2 symmetrically arranged on both sides of the upper middle part of the fuselage 1, two tail wings 3 arranged on both sides of the tail of the fuselage 1, a thrust propeller 6 arranged at the tail of the fuselage 1, and ailerons 4 arranged on the rear side of each wing 2. Each wing 2 is connected to the fuselage 1, each tail fin 3 is connected to the fuselage 1, and each thrust propeller 6 is connected to the fuselage 1. A folding mechanism 9 with elastic memory recovery is provided at the connection points of each wing 2 and fuselage 1, each tail fin 3 and fuselage 1, and each thrust propeller 6 and fuselage 1. The overall cross-section of the fuselage 1 has a trapezoidal structure with smaller upper sections and larger lower sections to reduce radar reflection coefficient.

[0045] Specifically, wings 2 and tail 3 are connected to fuselage 1 via a folding mechanism 9, which can meet the space requirements of the UAV in different working states, enabling small-space cellular storage, dense launch, and swarm warfare. Ailerons 4 are connected to their corresponding wings 2 to adjust the UAV's roll attitude.

[0046] Example 2 like Figures 1 to 8 As shown, this embodiment provides a stealthy foldable swarm drone, including a fuselage 1, two wings 2 symmetrically arranged on both sides of the upper middle part of the fuselage 1, two tail wings 3 arranged on both sides of the tail of the fuselage 1, a thrust propeller 6 arranged at the tail of the fuselage 1, and ailerons 4 arranged on the rear side of each wing 2. Each wing 2 is connected to the fuselage 1, each tail fin 3 is connected to the fuselage 1, and each thrust propeller 6 is connected to the fuselage 1. A folding mechanism 9 with elastic memory recovery is provided at the connection points of each wing 2 and fuselage 1, each tail fin 3 and fuselage 1, and each thrust propeller 6 and fuselage 1. The overall cross-section of the fuselage 1 has a trapezoidal structure with smaller upper sections and larger lower sections to reduce radar reflection coefficient.

[0047] The wing 2 adopts a swept-back high-wing configuration, and the tail 3 adopts a swept-back V-shaped configuration. The wing 2 folds backward through the folding mechanism 9, the tail 3 folds forward, and the thrust propeller 6 folds backward.

[0048] Wing 2 adopts a 30°~34° swept high-wing configuration.

[0049] Specifically, wing 2 provides the lift required for the UAV's flight. The shape and size of wing 2 have been precisely optimized to improve the lift coefficient and reduce induced drag. This design incorporates stealth features for wing 2, which is fixed to the fuselage 1 and adopts a 30°~34° swept high-wing configuration to reduce radar wave reflection intensity and enhance its stealth capabilities. Wingtip shaping and fine airfoil design improve the aircraft's lift-to-drag ratio. The shape and size of the tail fin 3 of wing 2 have also been precisely optimized to reduce the radar reflection coefficient.

[0050] Example 3 This embodiment is a further optimization based on embodiment 2, specifically: The tail fin 3 adopts a symmetrical V-shaped layout with a sweepback of 30°~34°, and the side of the fuselage 1 forms a 55° angle with the dihedral angle of the V-shaped tail fin 3.

[0051] Specifically, tail fin 3 is used to provide stability and maneuverability for the UAV, controlling its pitch and yaw angles. This design details the stealth design of tail fin 3. Tail fin 3 is fixed to the rear of fuselage 1 and adopts a symmetrical V-shaped layout with a 30°~34° sweepback. The side of fuselage 1 forms a 55° angle with the dihedral angle of the V-shaped tail fin 3, providing pitch and yaw control. Tail fin 3 maintains the same sweep angle as wing 2, regulating the direction of radar wave reflection to a unified direction, reducing the forward radar cross-section. The shape and size of tail fin 3 have been precisely optimized to reduce the radar reflection coefficient.

[0052] Example 4 This embodiment is a further optimization based on embodiment 2, specifically: The two wings 2 adopt a symmetrical folding form, with the upper and lower parts overlapping.

[0053] Specifically, the two wings adopt a symmetrical folding form, overlapping vertically, which can significantly increase the wing area.

[0054] Example 5 This embodiment is a further optimization based on embodiment 2, specifically: The nose of fuselage 1 has a parabolic outer contour. The fuselage 1 adopts a trapezoidal variable cross-section shape from front to back to reduce the forward radar cross-section. The rear of fuselage 1 has a tail cone rectification design to facilitate the loading of airborne equipment and maintain the balance and stability of the UAV.

[0055] Specifically, the streamlined design of fuselage 1 reduces aerodynamic drag during UAV flight, improving flight efficiency. Fuselage 1 adopts a trapezoidal shape with sloping sides for stealth design. Wings 2 and tail 3 adopt a regular echo direction for stealth design, and the angles of wings 2 and tail 3 have been precisely calculated. The dimensions of the thrust propeller 6 have also been precisely calculated.

[0056] Example 6 This embodiment is a further optimization based on embodiment 5, specifically: The fuselage 1 has an irregularly shaped rectifier protrusion on its underside, and several external interfaces 5 are provided on the irregularly shaped rectifier protrusion.

[0057] Specifically, the external interface 5 features an optimized design, with an irregularly shaped, streamlined protrusion on the underside of the fuselage 1. This protrusion allows for the expansion of external communication interfaces without requiring additional structural components. This design facilitates the expansion of external communication interfaces while maintaining the integrity of the airframe structure. External interface 5 enhances the versatility of the UAV's mission payload, data communication capabilities, and ease of use.

[0058] The shapes and angles of the fuselage 1 and external interface 5, wings 2 and tail 3 have been precisely calculated to enhance stealth capabilities and provide excellent lift-drag and handling characteristics. The dimensions of the thrust propeller 6 have been optimized.

[0059] Example 6 This embodiment is a further optimization based on embodiment 5, specifically: Each folding mechanism 9 includes a support shaft 10 fixed to the body 1, an elastic memory recovery component fixedly sleeved on the support shaft 10, a connecting part provided on the elastic memory component, and a wing locking pin 8 provided on the connecting part; The wings 2, tail 3, and thrust propeller 6 are glued or plugged into their respective connecting parts.

[0060] The elastic memory component includes a fixed sleeve fixedly sleeved on the support shaft 10, and multiple memory metal springs fixedly connected to the outer wall of the fixed sleeve in a circumferential manner. The other end of the memory metal springs is connected to the connecting part. The fixing sleeve, all memory metal springs, and connecting parts are integrally molded.

[0061] The connecting part is provided with a connecting groove that can be inserted or glued to the root of the wing surface 7. The wing surface locking pin 8 is provided on the connecting part near the root of the wing surface 7. The wing surface locking pin 8 includes a spring and a locking pin. The fuselage 1 is provided with a locking hole that cooperates with the wing surface locking pin 8 when the wing 2, tail 3, and thrust propeller 6 are unfolded. The fuselage 1 is also provided with a limiting mechanism for restraining the folded wing 2, tail 3, and thrust propeller 6.

[0062] Specifically, the elastic memory component adopts a structure combining memory metal and flat springs. The wing locking pin 8 is positioned on the connection point near the wing root of various wing surfaces to meet wing locking requirements. The folding drive device differs from traditional folding methods, using memory alloy metal as the power source for the torsional drive, resulting in a simple, compact, and highly reliable structure. The folding mechanism 9 utilizes the characteristic of the memory metal spring sheet to return to its initial state after deformation to achieve the wing's folding and unfolding function. The wing rotates around the support shaft 10, and the connection point is positioned using keys or pins, etc. The support shaft 10 remains stationary, and the wing locking pin 8 locks the wing in its unfolded position.

Claims

1. A stealthy, foldable swarm drone, characterized in that, It includes a fuselage (1), two wings (2) symmetrically arranged on both sides of the upper middle part of the fuselage (1), two tail wings (3) arranged on both sides of the tail of the fuselage (1), a thrust propeller (6) arranged at the tail of the fuselage (1), and ailerons (4) arranged on the rear side of each of the wings (2). Each of the wing (2) connected to the fuselage (1), each of the tail fins (3) connected to the fuselage (1), and each of the thrust propellers (6) connected to the fuselage (1) are provided with a folding mechanism (9) with elastic memory recovery. The fuselage (1) has an overall cross-section in the shape of a trapezoid with smaller upper sections and larger lower sections to reduce radar reflection coefficient.

2. The stealthy foldable swarm drone according to claim 1, characterized in that, The wing (2) adopts a swept-back high-wing configuration, and the tail fin (3) adopts a swept-back V-shaped configuration. The wing (2) is folded backward by the folding mechanism (9), the tail fin (3) is folded forward, and the thrust propeller (6) is folded backward.

3. A stealthy, foldable swarm drone according to claim 2, characterized in that, The wing (2) adopts a 30°~34° swept-back high-wing configuration.

4. A stealthy, foldable swarm drone according to claim 3, characterized in that, The tail fin (3) adopts a symmetrical V-shaped layout with a sweepback of 30°~34°, and the side of the fuselage (1) forms a 55° angle with the upper dihedral angle of the V-shaped tail fin (3).

5. A stealthy, foldable swarm drone according to claim 2, characterized in that, The two wings (2) are symmetrically folded and overlap vertically.

6. A stealthy, foldable swarm drone according to claim 1, characterized in that, The outer contour of the nose of the fuselage (1) is parabolic. The fuselage (1) adopts a trapezoidal variable cross-section shape from front to back to reduce the forward radar cross-section. The rear of the fuselage (1) is designed with a tail cone rectifier to facilitate the loading of airborne equipment and maintain the balance and stability of the UAV.

7. A stealthy, foldable swarm drone according to claim 1, characterized in that, The fuselage (1) has an irregularly shaped rectifier protrusion on its belly, and the irregularly shaped rectifier protrusion has several external interfaces (5).

8. A stealthy, foldable swarm drone according to claim 1, characterized in that, Each of the folding mechanisms (9) includes a support shaft (10) fixed on the fuselage (1), an elastic memory recovery member fixedly sleeved on the support shaft (10), a connecting part provided on the elastic memory member, and a wing locking pin (8) provided on the connecting part. The wings (2), the tail fin (3), and the thrust propeller (6) are bonded or inserted into their respective connecting parts.

9. A stealthy, foldable swarm drone according to claim 8, characterized in that, The elastic memory component includes a fixed sleeve fixedly sleeved on the support shaft (10), and multiple memory metal springs fixedly connected to the outer wall of the fixed sleeve in a circumferential manner. The other end of the memory metal springs is connected to the connecting part. The fixing sleeve, all the memory metal springs, and the connecting part are integrally formed.

10. A stealthy, foldable swarm drone according to claim 9, characterized in that, The connecting part is provided with a connecting groove that can be inserted or glued to the root of the wing surface (7). The wing surface locking pin (8) is provided on the connecting part near the root of the wing surface (7). The wing surface locking pin (8) includes a spring and a locking pin. The fuselage (1) is provided with locking holes that cooperate with the wing surface locking pin (8) in the unfolded state of the wing (2), the tail fin (3), and the thrust propeller (6). The fuselage (1) is also provided with a limiting mechanism for constraining the folded wing (2), the tail fin (3), and the thrust propeller (6).

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